Latest content added for UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)https://digital.library.unt.edu/explore/collections/NACA/browse/?sort=date_d&fq=str_title_serial:NACA+Research+Memorandums&display=list2011-11-17T22:13:23-06:00UNT LibrariesThis is a custom feed for browsing UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)Some Research on the Lift and Stability of Wing-Body Combinations2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53149/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53149/"><img alt="Some Research on the Lift and Stability of Wing-Body Combinations" title="Some Research on the Lift and Stability of Wing-Body Combinations" src="https://digital.library.unt.edu/ark:/67531/metadc53149/small/"/></a></p><p>The present paper summarizes and correlates broadly some of the research results applicable to fin-stabilized ammunition. The discussion and correlation are intended to be comprehensive, rather than detailed, in order to show general trends over the Mach number range up to 7.0. Some discussion of wings, bodies, and wing-body interference is presented, and a list of 179 papers containing further information is included. The present paper is intended to serve more as a bibliography and source of reference material than as a direct source of design information.</p>An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64660/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64660/"><img alt="An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes" title="An Analytical Evaluation of the Effects of an Aerodynamic Modification and of Stability Augmenters on the Pitch Behavior and Probable Pilot Opinion of Two Current Fighter Airplanes" src="https://digital.library.unt.edu/ark:/67531/metadc64660/small/"/></a></p><p>Memorandum presenting the effects of wing modification and stability augmentation on the computed longitudinal behavior in the pitch-up region and probable pilot opinion of the pitch-up characteristics of two current fighter airplanes. An exploration of the addition of a wing-leading edge is included. Results regarding computed pitch-up behavior and probable pilot opinion are provided.</p>Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.502011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53080/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53080/"><img alt="Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50" title="Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50" src="https://digital.library.unt.edu/ark:/67531/metadc53080/small/"/></a></p><p>Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.</p>Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64263/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64263/"><img alt="Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine" title="Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine" src="https://digital.library.unt.edu/ark:/67531/metadc64263/small/"/></a></p><p>Report presenting a determination of the characteristics velocity of liquid oxygen and gaseous hydrogen as a function of mixture ratio in a nominal 200-pound-thrust variable-length rocket engine. Fourteen injectors, which varied mixing and oxygen atomization, were investigated. The four types of injector designs included triplets of two hydrogen jets impinging on one oxygen jet, concentric injection with hydrogen surrounding a jet of oxygen, radial injection of oxygen with variations in hydrogen injection, and oxygen atomization by two impinging jets with variations in hydrogen injection.</p>Off-Design Performance of Divergent Ejectors2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52845/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52845/"><img alt="Off-Design Performance of Divergent Ejectors" title="Off-Design Performance of Divergent Ejectors" src="https://digital.library.unt.edu/ark:/67531/metadc52845/small/"/></a></p><p>Report presenting an investigation of the off-design performance of fixed- and variable-geometry divergent ejectors. Results regarding fixed geometry and low secondary flow, fixed geometry and high secondary flow, variable geometry and low secondary flow, variable geometry and high secondary flow, and ejectors with full afterburning are provided.</p>Off-Design Performance of Divergent Ejectors2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64402/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64402/"><img alt="Off-Design Performance of Divergent Ejectors" title="Off-Design Performance of Divergent Ejectors" src="https://digital.library.unt.edu/ark:/67531/metadc64402/small/"/></a></p><p>"The off-design performance of fixed- and of variable-geometry divergent ejectors was investigated. The ejectors, which were designed for turbojet operation at Mach 3, were investigated in the Mach number range of 0.8 to 2. The performance of a fixed-geometry ejector with high secondary-flow rates was competitive with that of more complex variable-geometry ejectors. Variable-geometry ejectors with compromises to reduce mechanical complexity produced performance reasonably close to that of an ideal variable ejector" (p. 1).</p>Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.82011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64417/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64417/"><img alt="Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8" title="Rocket-Model Investigation to Determine the Lift and Pitching Effectiveness of Small Pulse Rockets Exhausted From the Fuselage Over the Surface of an Adjacent Wing at Mach Numbers From 0.9 to 1.8" src="https://digital.library.unt.edu/ark:/67531/metadc64417/small/"/></a></p><p>Report presenting some experimental free-flight data at a range of Mach numbers regarding the normal force and pitching effectiveness of several small pulse rockets in the fuselage of a rocket propelled model. Wing-damping data was also obtained from the wing bending response to the pulse-rocket excitations, and longitudinal stability data was determined from the model response. Results regarding pulse-rocket effectiveness, wing damping, and model stability data are provided.</p>Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64240/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64240/"><img alt="Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination" title="Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination" src="https://digital.library.unt.edu/ark:/67531/metadc64240/small/"/></a></p><p>Report presenting an exploratory study of the screaming tendency of the gaseous-hydrogen-liquid-oxygen propellant combination in 200-pound-thrust rocket engines. Four injector classes in a total of 12 different configurations were tested in a variety of chamber lengths over the usable mixture-ratio range. Results regarding acoustic oscillations, unclassified oscillations, driving and damping mechanisms, and effects of screaming on heat transfer are provided.</p>Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52986/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52986/"><img alt="Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude" title="Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude" src="https://digital.library.unt.edu/ark:/67531/metadc52986/small/"/></a></p><p>Memorandum presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process, which was inhibited by water vapor from compressor-inlet injection. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the effects of hydrogen injection on afterburner performance and effect of aluminum trimethyl afterburner fuel additive on performance are provided.</p>Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64354/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64354/"><img alt="Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude" title="Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude" src="https://digital.library.unt.edu/ark:/67531/metadc64354/small/"/></a></p><p>Report presenting an investigation in an altitude test chamber to evaluate the use of highly reactive chemicals injected into a turbojet afterburner to promote the combustion process. The chemicals evaluated were commercial hydrogen and aluminum trimethyl. Results regarding the afterburner efficiency, afterburner stability limits, afterburner-outlet total temperature, and an application of the results to other systems are provided.</p>Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53283/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53283/"><img alt="Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield" title="Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield" src="https://digital.library.unt.edu/ark:/67531/metadc53283/small/"/></a></p><p>Report discussing a study of the effects of puncturing the heat shield of an intercontinental-ballistic-missile warhead by small projectiles. Calculations were created for both rod and sphere projectiles and experimental testing was performed on a missile model with holes drilled in the heat shield. The possibility that a projectile could have enough energy to cause mechanical damage to the interior of the warhead is also presented.</p>Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64337/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64337/"><img alt="Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination" title="Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination" src="https://digital.library.unt.edu/ark:/67531/metadc64337/small/"/></a></p><p>From Introduction: "Wind-tunnel and flight tests have shown that conical leading-edge camber on a thin low-aspect-ratio delta wing results in increasing the lift-drag ratio at transonic and low supersonic speeds (refs. 1 and 2). References 3 and 4 present the results of two previous investigations of this general program. A more detailed analysis of the pressure distributions of reference 5 is presented herein in terms of total section loads and overall wing-body characteristics."</p>Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.892011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52942/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52942/"><img alt="Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.89" title="Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.89" src="https://digital.library.unt.edu/ark:/67531/metadc52942/small/"/></a></p><p>Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.</p>Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64423/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64423/"><img alt="Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices" title="Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices" src="https://digital.library.unt.edu/ark:/67531/metadc64423/small/"/></a></p><p>From Summary: "An investigation was conducted to determine the longitudinal characteristics of an airplane model with a 35 degree swept wing of aspect ratio 7 and four pylon-mounted nacelles. Several leading-edge configurations were studied in conjunction with double-slotted trailing-edge flaps. Three-component longitudinal data are presented. In general, the test Reynolds number was about 4.8 x 10(exp 6), but for selected configurations, data for Reynolds number ranges from 2.8 to 8 x 10(exp 6) are included."</p>Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.52011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64332/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64332/"><img alt="Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5" title="Static and dynamic-rotary stability derivatives of an airplane model with an unswept wing and a high horizontal tail at Mach numbers of 2.5, 3.0, and 3.5" src="https://digital.library.unt.edu/ark:/67531/metadc64332/small/"/></a></p><p>Report presenting the static and dynamic-rotary stability derivatives for an airplane with an unswept wing and a high horizontal tail as determined in wind-tunnel tests at 3 Mach numbers. The tail contribution to stability was found to not be predicted by the simplified theoretical methods used in this report. Results regarding the longitudinal derivatives, sideslip derivatives, yawing derivatives, rolling derivatives, and variation of static derivatives with Mach number.</p>Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53222/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53222/"><img alt="Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet" title="Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet" src="https://digital.library.unt.edu/ark:/67531/metadc53222/small/"/></a></p><p>Report presenting an investigation of the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in the supersonic wind tunnel. The investigation was carried out to determine the performance penalties associated with spike-tip and cowl-lip blunting. Results regarding the effect of rounding the spike tip on inlet performance, overall drag coefficients, flow distortion, and Schileren photographs are provided.</p>Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64349/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64349/"><img alt="Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet" title="Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet" src="https://digital.library.unt.edu/ark:/67531/metadc64349/small/"/></a></p><p>Report presenting the effect of inlet component blunting on performance using an axisymmetric external-compression inlet in order to determine the performance penalties associated with spike-tip and cowl-lip blunting. The data can be used as a design guide for blunt inlet components applicable to cooling techniques. Results regarding the effect of tip rounding, drag coefficients, flow distortion, lip blunting, and Schileren photographs are provided.</p>Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.952011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53218/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53218/"><img alt="Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95" title="Experimental Investigation of Effect of Spike- Tip and Cowl-Lip Blunting on the Internal Performance of a Two-Cone Cylindrical-Cowl Inlet at Mach Number 4.95" src="https://digital.library.unt.edu/ark:/67531/metadc53218/small/"/></a></p><p>Memorandum presenting the effect of blunting on the internal performance of a two-cone inlet with an internally cylindrical cowl investigated experimentally at Mach number 4.95. Total-pressure-recovery and mass-flow data were obtained for a range of spike and cowl bluntness.</p>Experimental Study of Ballistic-Missile Base Heating with Operating Rocket2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52877/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52877/"><img alt="Experimental Study of Ballistic-Missile Base Heating with Operating Rocket" title="Experimental Study of Ballistic-Missile Base Heating with Operating Rocket" src="https://digital.library.unt.edu/ark:/67531/metadc52877/small/"/></a></p><p>"A rocket of the 1000-pound-thrust class using liquid oxygen and JP-4 fuel as propellant was installed in the Lewis 8- by 6-foot tunnel to permit a controlled study of some of the factors affecting the heating of a rocket-missile base. Temperatures measured in the base region are presented from findings of three motor extension lengths relative to the base. Data are also presented for two combustion efficiency levels in the rocket motor" (p. 1).</p>Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.02011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52979/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52979/"><img alt="Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0" title="Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0" src="https://digital.library.unt.edu/ark:/67531/metadc52979/small/"/></a></p><p>"Investigation of the control parameters of an external-internal compression inlet indicates that the cowl-lip shock provides a signal to position the spike and to start the inlet over a Mach number range from 2.1 to 3.0. Use of a single fixed probe position to control the spike over the range of conditions resulted in a 3.7-count loss in total-pressure recovery at Mach 3.0 and 0 deg angle of attack. Three separate shock-sensing-probe positions were required to set the spike for peak recovery from Mach 2.1 to 3.0 and angles of attack from 0 deg to 6 deg" (p. 1).</p>Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 182011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53064/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53064/"><img alt="Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18" title="Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18" src="https://digital.library.unt.edu/ark:/67531/metadc53064/small/"/></a></p><p>Memorandum presenting a study of aerodynamic performance and static stability and control at hypersonic speeds. In the first part of the study, the effect of interference lift is investigated by tests of asymmetric models with conical fuselages and arrow plan-form wings. In the second part, the aerodynamic performance and static stability and control characteristics of a hypersonic glider are investigated in somewhat greater detail.</p>Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 182011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64409/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64409/"><img alt="Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18" title="Aerodynamic Performance and Static Stability and Control of Flat-Top Hypersonic Gliders at Mach Numbers From 0.6 to 18" src="https://digital.library.unt.edu/ark:/67531/metadc64409/small/"/></a></p><p>Report presenting a study of the aerodynamic performance and static stability and control at hypersonic speed using flat-top hypersonic gliders.</p>Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52945/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52945/"><img alt="Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces" title="Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces" src="https://digital.library.unt.edu/ark:/67531/metadc52945/small/"/></a></p><p>Results regarding a wind-tunnel investigation of wingless missile configurations with cylindrical bodies and conical or hemispherical noses, extensible control surfaces aft of the nose, and tails consisting of eight low-aspect-ratio triangular or rectangular fins. Normal-force, axial-force, and pitching-moment coefficients were obtained for several control deflections for Mach numbers 1.2 and 1.9.</p>Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane2011-11-17T17:13:32-06:00https://digital.library.unt.edu/ark:/67531/metadc62852/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc62852/"><img alt="Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane" title="Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc62852/small/"/></a></p><p>"The buffeting loads acting on the wing and horizontal tail of a 1/4-scale model of the X-1E airplane have been measured in the Langley 16-foot transonic tunnel in the Mach number range from 0.40 to 0.90. When the buffeting loads were reduced to a nondimensional aerodynamic coefficient of buffeting intensity, it was found that the maximum buffeting intensity of the horizontal tail was about twice as large as that of the wing. Comparison of power spectra of buffeting loads acting on the horizontal tail of the airplane and of the model indicated that the model horizontal tail, which was of conventional force-test-model design, responded in an entirely different mode than did the airplane" (p. 1).</p>Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.142011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64415/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64415/"><img alt="Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.14" title="Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.14" src="https://digital.library.unt.edu/ark:/67531/metadc64415/small/"/></a></p><p>Memorandum presenting a discussion of a fineness-ratio-2.6 bluff shape with an x(exp 1/10) nose and a 5 degree flare extending the entire body length and a fineness-ratio-2.5 bluff shape with an x(exp 1/10) nose and a square base with sides equal to the diameter of the cylindrical forebody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force and moment coefficients, and plots of the longitudinal-force coefficient, rolling velocity, aerodynamic center, normal-force-curve slope, and dynamic stability are presented.</p>Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 22011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52947/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52947/"><img alt="Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2" title="Design and Experimental Investigation of a Single-Stage Turbine With a Rotor Entering Relative Mach Number of 2" src="https://digital.library.unt.edu/ark:/67531/metadc52947/small/"/></a></p><p>Memorandum presenting a design and experimental investigation of a single-stage supersonic turbine. The turbine was designed for a rotor entering relative Mach number of 2. Results regarding the overall turbine performance, outer-wall static-pressure variation, momentum-loss considerations, effect of rotor modifications, and supersonic starting are provided.</p>Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.502011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52983/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52983/"><img alt="Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50" title="Performance of an Isentropic, All-Internal-Contraction, Axisymmetric Inlet Designed for Mach 2.50" src="https://digital.library.unt.edu/ark:/67531/metadc52983/small/"/></a></p><p>Memorandum presenting an experimental investigation of an internal-contraction, axially symmetric inlet with isentropic compression surfaces on both the cowl and centerbody conducted over a range of Mach numbers from 2.0 to 2.7 at angles of attack from 0 to 6 degrees. The study was made to determine the optimum bleed system, together with a method of controlling the inlet.</p>The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64322/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64322/"><img alt="The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane" title="The static and dynamic-rotary stability derivatives at subsonic speeds of a model of the X-15 research airplane" src="https://digital.library.unt.edu/ark:/67531/metadc64322/small/"/></a></p><p>Report presenting measurements in a wind tunnel of the subsonic static and dynamic-rotary stability derivatives of a model of an airplane designed to fly at high supersonic speeds and high altitudes. The effects of flaps and landing gear, speed brakes, and several model components are included in the results as well as the stability characteristics of the model.</p>Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64318/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64318/"><img alt="Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration" title="Wind-tunnel investigation of the low-speed aerodynamic characteristics of a hypersonic glider configuration" src="https://digital.library.unt.edu/ark:/67531/metadc64318/small/"/></a></p><p>Report presenting a wind-tunnel investigation of the low-speed aerodynamic characteristics of an airplane configuration designed to obtain high lift-drag ratios at hypersonic speeds. The power-off landing of this aircraft would be difficult due to the high sinking speeds inherent in the design. Results regarding the longitudinal characteristics, lateral characteristics, and landing considerations are provided.</p>Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64406/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64406/"><img alt="Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight" title="Aerodynamic Characteristics at Mach Numbers From 2.5 to 3.5 of a Canard Bomber Configuration Designed for Supersonic Cruise Flight" src="https://digital.library.unt.edu/ark:/67531/metadc64406/small/"/></a></p><p>Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.</p>A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52833/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52833/"><img alt="A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance" title="A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance" src="https://digital.library.unt.edu/ark:/67531/metadc52833/small/"/></a></p><p>Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.</p>Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 102011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52943/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52943/"><img alt="Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10" title="Free-Flight Investigation of Aerodynamic Heat Transfer to a Simulated Glide-Rocket Shape at Mach Numbers up to 10" src="https://digital.library.unt.edu/ark:/67531/metadc52943/small/"/></a></p><p>"Heat-transfer measurements were made on a simulated glide-rocket shape in free flight at Mach numbers up to 10 and free-stream Reynolds numbers of 2 x 10 based on distance along surface from apex and 3 x 10 based on nominal leading-edge diameter. The model simulated the bottom of a 75 deg delta wing at 80 deg angle of attack. The data indicated that for the test conditions a modified three-dimensional stagnation-point theory will predict to reasonable engineering accuracy the heating on a highly swept wing leading edge, the heating being reduced by sweep by the 3/2 power of the cosine of the sweep angle" (p. 1).</p>Wind-Tunnel Investigation at Mach Numbers From 0.6 to 1.4 of Several Ejected Pilot-Seat Models2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64259/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64259/"><img alt="Wind-Tunnel Investigation at Mach Numbers From 0.6 to 1.4 of Several Ejected Pilot-Seat Models" title="Wind-Tunnel Investigation at Mach Numbers From 0.6 to 1.4 of Several Ejected Pilot-Seat Models" src="https://digital.library.unt.edu/ark:/67531/metadc64259/small/"/></a></p><p>"The results are presented of an experimental investigation conducted to determine the static longitudinal and lateral-direction aerodynamic characteristics of basic and modified versions of a conventional upward ejected pilot-seat combination, a sled-type upward ejected pilot-seat combination, and a downward ejected pilot-seat combination" (p. 1). The drag coefficient, lift coefficient, rolling-moment coefficient, pitching-moment coefficient, yawing-moment coefficient, and side-force coefficient are provided.</p>Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64250/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64250/"><img alt="Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane" title="Wind-tunnel investigation of the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane" src="https://digital.library.unt.edu/ark:/67531/metadc64250/small/"/></a></p><p>Memorandum presenting an investigation conducted in the full-scale tunnel to determine the aerodynamic and structural deflection characteristics of the Goodyear Inflatoplane over a range of test velocities from minimum stall speed up to speeds giving load factors for wing buckling. The airplane was developed as a potential way to rescue downed pilots in enemy territory. An exploration of the stability, stalling characteristics, buckling, and chosen configuration is provided.</p>Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53282/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53282/"><img alt="Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane" title="Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc53282/small/"/></a></p><p>Report discussing an investigation of the dynamic stability and control characteristics of a model of the Ryan X-13 jet VTOL airplane in hovering and transition flight. Flight control was smooth and easy without the gyroscopic effects of the engine represented, but adding a simulation of the gyroscopic effects caused the plane to become uncontrollable in hovering flight without artificial stabilization. The transition was found to be easy to perform with and without gyroscopic effects, but the model had a tendency to fly in roll and slideslipped attitudes.</p>Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64246/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64246/"><img alt="Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades" title="Comparison of Calculated and Experimental Temperatures and Coolant Pressure Losses for a Cascade of Small Air-Cooled Turbine Rotor Blades" src="https://digital.library.unt.edu/ark:/67531/metadc64246/small/"/></a></p><p>From Summary: "Average spanwise blade temperatures and cooling-air pressure losses through a small (1.4-in, span, 0.7-in, chord) air-cooled turbine blade were calculated and are compared with experimental nonrotating cascade data. Two methods of calculating the blade spanwise metal temperature distributions are presented. The method which considered the effect of the length-to-diameter ratio of the coolant passage on the blade-to-coolant heat-transfer coefficient and assumed constant coolant properties based on the coolant bulk temperature gave the best agreement with experimental data."</p>Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc52872/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc52872/"><img alt="Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine" title="Comparison of Injectors With a 200-Pound-Thrust Ammonia-Oxygen Engine" src="https://digital.library.unt.edu/ark:/67531/metadc52872/small/"/></a></p><p>"Characteristic exhaust velocity was measured for a small range of mixture ratios with four different injectors. Performances of parallel-sheet, like-on-like, and triplet injectors were about the same, but a parallel-jet injector had a much lower performance. Performance values for ammonia-oxygen were slightly lower than for heptane-oxygen" (p. 1).</p>Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area2011-11-16T07:33:14-06:00https://digital.library.unt.edu/ark:/67531/metadc58374/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc58374/"><img alt="Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area" title="Design and Experimental Performance of a 0.35 Hub-Tip Radius Ratio Transonic Axial-Flow-Compressor Rotor Designed for 40 Pounds Per Second Per Unit Frontal Area" src="https://digital.library.unt.edu/ark:/67531/metadc58374/small/"/></a></p><p>Memorandum presenting an investigation to determine the feasibility of a high-performance transonic axial-flow compressor stage with a weight flow of 40 pounds per second per square foot of frontal area. A transonic axial-flow inlet stage with a hub-tip ratio of 0.35 and an axial Mach number of approximately 0.75 was designed and fabricated. Results regarding overall rotor performance, flow parameters, radial matching of blade-element sections, and comparison of blade-element parameters with design rules are provided.</p>Thermal reaction of diborane with trimethylborane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64257/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64257/"><img alt="Thermal reaction of diborane with trimethylborane" title="Thermal reaction of diborane with trimethylborane" src="https://digital.library.unt.edu/ark:/67531/metadc64257/small/"/></a></p><p>Report presenting testing of diborane and trimethylbornae in a tube at 235 to 300 degrees Celsius in the presence of hydrogen. Methylpentaboranes were produced and separated in a specially designed vacuum fractionation column. Results indicated that two isomers of monomethylpentaborane were isolated and that one had not been previously reported on.</p>Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64300/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64300/"><img alt="Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream" title="Experimental investigation of the effect of yaw on rates of heat transfer to transverse circular cylinders in a 6500-foot-per-second hypersonic air stream" src="https://digital.library.unt.edu/ark:/67531/metadc64300/small/"/></a></p><p>Report describing equipment that can be used to shock-compress air by helium to 3660 degrees Rankine to generate a 6500-foot-per-second air stream with a flow duration of 40 milliseconds. The influence of yaw on rates of heat transfer to the same circular cylinders was investigated at angles of yaw up to 70 degrees.</p>Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64277/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64277/"><img alt="Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests" title="Flight Investigation of a Full-Scale Aircraft Ejector with Various Spacing Ratios and Correlation with Small-Scale Tests" src="https://digital.library.unt.edu/ark:/67531/metadc64277/small/"/></a></p><p>Memorandum presenting a flight investigation to determine the thrust and pumping characteristics of a family of aircraft exhaust ejectors. Information was obtained on the variation of these characteristics with changes in engine power, flight Mach number, and ejector spacing ratio, and these results were compared to small-scale tests. Results were also obtained showing how a swinging survey probe can be used as a device for calibrating a tail-pipe pressure probe for the measurement of thrust and air flow.</p>Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64256/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64256/"><img alt="Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow" title="Forces and pitching moments on an aspect-ratio-3.1 wing-body combination at Mach numbers from 2.5 to 3.5 and sublimation studies of the effect of single-elements roughness on the boundary-layer flow" src="https://digital.library.unt.edu/ark:/67531/metadc64256/small/"/></a></p><p>Report presenting lift, drag, and pitching-moment characteristics for a wing-body combination for a range of Mach numbers. The wing had an aspect ratio of 3.1, a sweepback of the leading edge of 19.1 degrees, a taper ratio of 0.39, and a biconvex profile with a thickness of 3 percent of the chord. Results regarding aerodynamic characteristics and visual-flow studies are provided.</p>Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64343/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64343/"><img alt="Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight" title="Investigation of a Tilting-Wing Vertical-Take-Off-and-Landing Jet Airplane Model in Hovering and Transition Flight" src="https://digital.library.unt.edu/ark:/67531/metadc64343/small/"/></a></p><p>Report presenting the results of an investigation of the dynamic stability and controllability of a proposed supersonic-cruise, vertical-take-off-and-landing airplane configuration with a tilting wing and engines. The configuration tested was found to have satisfactory take-off, landing, and hovering characteristics. Information about transition flight, including stability and control characteristics, is provided.</p>Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile2011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53013/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53013/"><img alt="Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile" title="Summary of Flight Data Obtained From 0.12-Scale Rocket-Powered Models of the Chance Vought Regulus 2 Missile" src="https://digital.library.unt.edu/ark:/67531/metadc53013/small/"/></a></p><p>Report discussing the longitudinal static and dynamic stability, overall duct performance, drag, and some static and dynamic lateral-stability data obtained from testing of the Chance Vought Regulus II missile. Five different models with various modifications were used in the investigation.</p>An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64319/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64319/"><img alt="An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression" title="An Experimental Investigation of Two Internal-Compression Air-Inlet Designs Which Use Fluid Boundaries as a Means of Supersonic Compression" src="https://digital.library.unt.edu/ark:/67531/metadc64319/small/"/></a></p><p>Report presenting an investigation of the internal-flow characteristics of two novel designs of internal-compression air inlets in the supersonic blowdown tunnel. A longitudinally slotted contracting channel and effective contracting channel formed by the natural thickening of the boundary layer in a confined channel can be used to obtain pressure recoveries at a satisfactory level.</p>Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.082011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64289/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64289/"><img alt="Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08" title="Longitudinal and lateral aerodynamic characteristics at combined angles of attack and sideslip of a generalized missile model having a rectangular wing at a Mach number of 4.08" src="https://digital.library.unt.edu/ark:/67531/metadc64289/small/"/></a></p><p>Report presenting an investigation in the 9- by 9-inch Mach number 4 blowdown jet on a generalized body-wing-tail missilelike configuration to determine the source of the adverse rolling moment due to yaw experienced by this type of configuration with lifting surfaces and ventral and dorsal tail surfaces. Results regarding the longitudinal characteristics and lateral characteristics are provided.</p>Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.02011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64053/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64053/"><img alt="Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0" title="Use of Shock-Trap Bleed to Improve Pressure Recovery of Fixed-and Variable-Capture-Area Internal-Contraction Inlets; Mach Number 2.0 to 3.0" src="https://digital.library.unt.edu/ark:/67531/metadc64053/small/"/></a></p><p>Report presenting an investigation of two internal-contraction inlets in the block tunnel. The fixed inlet was tested at Mach number 2.94 with a conventional ram-scoop bleed and a shock-trap bleed. Results regarding the fixed-capture-area inlet and variable-capture-area inlet are provided.</p>Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64307/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64307/"><img alt="Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds" title="Wind-Tunnel Investigation of the Effect of Sweep and Taper Ratio on Effectiveness of Spoiler-Slot-Deflector Controls on Aspect-Ratio-4 Wings at Transonic Speeds" src="https://digital.library.unt.edu/ark:/67531/metadc64307/small/"/></a></p><p>Report presenting a wind-tunnel investigation performed in the high-speed tunnel to study the effect of wing sweep and taper ratio on spoiler-slot-deflector control effectiveness. All of the wings tested were aspect-ratio-4 and had NACA 65A004 airfoil sections as well as a variety of sweep angles, taper ratios, and spoiler projections. The results are presented without analysis.</p>Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 142011-11-11T19:22:00-06:00https://digital.library.unt.edu/ark:/67531/metadc53190/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc53190/"><img alt="Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14" title="Aerodynamic Heating of Blunt Nose Shapes at Mach Numbers Up to 14" src="https://digital.library.unt.edu/ark:/67531/metadc53190/small/"/></a></p><p>From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."</p>Aerodynamic heating of blunt nose shapes at Mach numbers up to 142011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc64156/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc64156/"><img alt="Aerodynamic heating of blunt nose shapes at Mach numbers up to 14" title="Aerodynamic heating of blunt nose shapes at Mach numbers up to 14" src="https://digital.library.unt.edu/ark:/67531/metadc64156/small/"/></a></p><p>From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."</p>