Latest content added for UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)https://digital.library.unt.edu/explore/collections/NACA/browse/?fq=untl_decade:1950-1959&display=list2014-09-25T20:32:43-05:00UNT LibrariesThis is a custom feed for browsing UNT Digital Library Collection: National Advisory Committee for Aeronautics (NACA)A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow2014-09-25T20:32:43-05:00https://digital.library.unt.edu/ark:/67531/metadc172515/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc172515/"><img alt="A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow" title="A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow" src="https://digital.library.unt.edu/ark:/67531/metadc172515/small/"/></a></p><p>Comparison of free-molecule-flow theory with the results of wind-tunnel tests performed to determine the drag and temperature-rise characteristics of a transverse circular cylinder.</p>Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method2014-09-25T20:32:43-05:00https://digital.library.unt.edu/ark:/67531/metadc172521/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc172521/"><img alt="Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method" title="Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method" src="https://digital.library.unt.edu/ark:/67531/metadc172521/small/"/></a></p><p>Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers.</p>Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section2014-09-25T20:32:43-05:00https://digital.library.unt.edu/ark:/67531/metadc100822/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc100822/"><img alt="Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section" title="Tables for the Computation of Wave Drag of Arrow Wings of Arbitrary Airfoil Section" src="https://digital.library.unt.edu/ark:/67531/metadc100822/small/"/></a></p><p>Tables and computing instructions for the rapid evaluation of the wave drag of delta wings and of arrow wings having a ration of the tangent of the trailing-edge sweep angle to the tangent of the leading-edge sweep angle in the range from -1.0 to 0.8. The tables cover a range of both subsonic and supersonic leading edges.</p>Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique2014-09-25T20:32:43-05:00https://digital.library.unt.edu/ark:/67531/metadc100823/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc100823/"><img alt="Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique" title="Summary of 65-Series Compressor-Blade Low-Speed Cascade Data by Use of the Carpet-Plotting Technique" src="https://digital.library.unt.edu/ark:/67531/metadc100823/small/"/></a></p><p>Carpet plots included permit the selection of the blade camber and the design angle of attack required to fulfill a design vector diagram. Other carpet plots provide means for the prediction of off-design turning angles.</p>Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades2014-09-25T20:32:43-05:00https://digital.library.unt.edu/ark:/67531/metadc100824/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc100824/"><img alt="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" title="Average Outside-Surface Heat-Transfer Coefficients and Velocity Distributions for Heated and Cooled Impulse Turbine Blades in Static Cascades" src="https://digital.library.unt.edu/ark:/67531/metadc100824/small/"/></a></p><p>Heat-transfer investigation conducted on cooled as well heated impulse-type turbine blades in a static cascade to determine the effect of direction of heat flow on convective heat-transfer coefficients.</p>Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 12952014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279525/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279525/"><img alt="Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 1295" title="Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 1295" src="https://digital.library.unt.edu/ark:/67531/metadc279525/small/"/></a></p><p>Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.</p>Investigations toward simplification of missile control systems2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279465/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279465/"><img alt="Investigations toward simplification of missile control systems" title="Investigations toward simplification of missile control systems" src="https://digital.library.unt.edu/ark:/67531/metadc279465/small/"/></a></p><p>Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.</p>Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279554/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279554/"><img alt="Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings" title="Comparison of the performance of a helicopter-type ram-jet engine under various centrifugal loadings" src="https://digital.library.unt.edu/ark:/67531/metadc279554/small/"/></a></p><p>Report presenting an investigation of an 18-foot-radius helicopter rotor powered by tip-mounted ramjet engines in the helicopter test tower. The engine performance is compared with the performance determined in a previous investigation of a 9-foot-radius rotor with the same engines at similar speeds but with twice the centrifugal forces. Results regarding the propulsive characteristics, minimum specific fuel consumption and corresponding propulsive thrust, and operational characteristics are provided.</p>Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279644/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279644/"><img alt="Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data" title="Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data" src="https://digital.library.unt.edu/ark:/67531/metadc279644/small/"/></a></p><p>Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.</p>Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279650/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279650/"><img alt="Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds" title="Wind-Tunnel Investigation to Determine the Horizontal- and Vertical-Tail Contributions to the Static Lateral Stability Characteristics of a Complete-Model Swept-Wing Configuration at High Subsonic Speeds" src="https://digital.library.unt.edu/ark:/67531/metadc279650/small/"/></a></p><p>Results regarding an investigation to determine the horizontal- and vertical-tail contributions to the static lateral stability of a complete-model swept-wing configuration at high subsonic speeds. Generally, Mach number effects within the range studied and wing effects on the tail contribution were small and the overall trends of the data of the present investigation agreed with those which have been established at low speeds.</p>Reciprocity relations in aerodynamics2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279660/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279660/"><img alt="Reciprocity relations in aerodynamics" title="Reciprocity relations in aerodynamics" src="https://digital.library.unt.edu/ark:/67531/metadc279660/small/"/></a></p><p>From Introduction: "The purpose of the present paper is twofold. First, a close connection will be established between reverse-flow theorems in subsonic and supersonic, steady-state wing theory and known reciprocity relations between two solutions of the equation the flow field."</p>Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.262014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279664/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279664/"><img alt="Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26" title="Rocket-Model Investigation to Determine the Hinge-Moment and Normal-Force Properties of a Full-Span, Constant-Chord, Partially Balanced Trailing-Edge Control on a 60 Degree Clipped Delta Wing Between Mach Numbers of 0.50 and 1.26" src="https://digital.library.unt.edu/ark:/67531/metadc279664/small/"/></a></p><p>Report presenting a free-flight investigation of a rocket-powered research model to determine the hinge-moment and normal-force characteristics of a trailing-edge control on a delta wing between Mach numbers of 0.50 and 1.26. The hinge-line location of 40 percent control chord satisfactorily reduced the high hinge moments associated with plain flap-type controls. Results regarding hinge moments and normal force are provided.</p>A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279618/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279618/"><img alt="A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees" title="A pressure-distribution investigation of a fineness-ratio-12.2 parabolic body of revolution (NACA RM-10) at M = 1.59 and angles of attack up to 36 degrees" src="https://digital.library.unt.edu/ark:/67531/metadc279618/small/"/></a></p><p>Report presenting a pressure-distribution investigation of a parabolic body of revolution with a fineness ratio of 12.2, which was performed in the 4- by 4-foot supersonic tunnel at Mach number 1.59 and Reynolds number 3.6 x 10(sub 6), based on body length, for a range of angles of attack. Results regarding basic pressures, aerodynamic coefficients, asymmetrical pressures, comparison of experimental and theoretical pressures, artificial roughness, section coefficients, and body coefficients are provided.</p>A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279629/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279629/"><img alt="A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel" title="A study of the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel" src="https://digital.library.unt.edu/ark:/67531/metadc279629/small/"/></a></p><p>Report presenting an investigation to study the use of various high-lift devices on the horizontal tail of a canard airplane model as a means of increasing the allowable center-of-gravity travel. The results indicated that the large increases in allowable center-of-gravity travel could be obtained using the devices. Results regarding the basic aerodynamic data, effect of tail configuration on the allowable center-of-gravity travel, and a comparison of measured and predicted values of the allowable center-of-gravity travel are provided.</p>The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279634/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279634/"><img alt="The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow" title="The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow" src="https://digital.library.unt.edu/ark:/67531/metadc279634/small/"/></a></p><p>Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.</p>A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279491/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279491/"><img alt="A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition" title="A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition" src="https://digital.library.unt.edu/ark:/67531/metadc279491/small/"/></a></p><p>Report describing the effects of an area of roughness on the velocity and turbulence measurements of an airfoil. It details the effects of the size, location, and height of the roughness on the Reynolds number. From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition."</p>Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279567/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279567/"><img alt="Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel" title="Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (With Fins) at a Mach Number of 1.62 in the Langley 9-Inch Supersonic Tunnel" src="https://digital.library.unt.edu/ark:/67531/metadc279567/small/"/></a></p><p>Report presenting an investigation of a fin-stabilized scale model of the NACA RM-10 missile at a Mach number of 1.62. Measurements were made of the lift, drag, and pitching moment of the finned body over a range of angles of attack. Comparisons with the results from other testing facilities are also provided.</p>Icing-Protection Requirements for Reciprocating-Engine Induction Systems2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279668/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279668/"><img alt="Icing-Protection Requirements for Reciprocating-Engine Induction Systems" title="Icing-Protection Requirements for Reciprocating-Engine Induction Systems" src="https://digital.library.unt.edu/ark:/67531/metadc279668/small/"/></a></p><p>Report presenting an investigation of the icing of aircraft-engine induction systems. Criterions for safe operation and for the design of new induction system are established through the investigation. The results were obtained from laboratory investigations of carburetor-supercharger combinations, wind-tunnel investigations of air scoops, multicylinder-engine studies, and flight investigations.</p>An experimental study of five annular air inlet configurations at subsonic and transonic speeds2014-03-30T18:00:15-05:00https://digital.library.unt.edu/ark:/67531/metadc279680/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc279680/"><img alt="An experimental study of five annular air inlet configurations at subsonic and transonic speeds" title="An experimental study of five annular air inlet configurations at subsonic and transonic speeds" src="https://digital.library.unt.edu/ark:/67531/metadc279680/small/"/></a></p><p>Report presenting an investigation of an NACA 1-80-100 nose inlet fitted alternately with an elliptical, a parabolic, a 14 degree-inch conical, and a 22 degree-inch conical central body at subsonic and transonic speeds in the 8-foot transonic tunnel. Drag, surface-pressure, and pressure-recovery measurements were obtained at 0 degrees angle of attack through a range of Mach numbers. Results regarding tunnel boundary interference, surface-pressure distribution, external drag, pressure recovery, and propulsive thrust comparison are provided.</p>Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig2014-03-22T10:27:53-05:00https://digital.library.unt.edu/ark:/67531/metadc277492/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc277492/"><img alt="Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig" title="Comparison of High-Speed Operating Characteristics of Size 215 Cylindrical-Roller Bearings as Determined in Turbojet Engine and in Laboratory Test Rig" src="https://digital.library.unt.edu/ark:/67531/metadc277492/small/"/></a></p><p>A comparison of the operating characteristics of 75-millimeter-bore (size 215) cylindrical-roller one-piece inner-race-riding cage-type bearings was made by means of a laboratory test rig and a turbojet engine. Cooling correlation parameters were determined by means of dimensional analysis, and the generalized results for both the inner- and the outer-race bearing operating temperatures are computed for the laboratory test rig and the turbojet engine. A method is given that enables the designer to predict the inner- and outer-race turbine roller-bearing temperatures from single curves, regardless of variations in speed, load, oil flow, oil inlet temperature, oil inlet viscosity, oil-jet diameter, or any combination of these parameters.</p>Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61476/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61476/"><img alt="Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip" title="Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip" src="https://digital.library.unt.edu/ark:/67531/metadc61476/small/"/></a></p><p>From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."</p>Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61479/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61479/"><img alt="Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph" title="Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph" src="https://digital.library.unt.edu/ark:/67531/metadc61479/small/"/></a></p><p>Report presenting testing of a towed airplane model in the 19-foot pressure tunnel in conjunction with the development of a flutter testing technique. The model was equipped with an autopilot to keep the model flying straight and level in the tunnel while restrained only in drag. Results regarding period and cycles to damp to half amplitude, time histories, and motions of the flexible wing model are provided.</p>Simulator studies of a simple homing system2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61534/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61534/"><img alt="Simulator studies of a simple homing system" title="Simulator studies of a simple homing system" src="https://digital.library.unt.edu/ark:/67531/metadc61534/small/"/></a></p><p>Report presenting simulator studies of a homing missile pursuing a constant-velocity nonmaneuvering target. The missile dynamics in pitch and roll, seeker method of deflection and control, and the missile-target geometry were simulated to determine whether the method of control and detection in conjunction with the missile dynamics were feasible.</p>An Investigation of Loads on Ailerons at Transonic Speeds2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61548/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61548/"><img alt="An Investigation of Loads on Ailerons at Transonic Speeds" title="An Investigation of Loads on Ailerons at Transonic Speeds" src="https://digital.library.unt.edu/ark:/67531/metadc61548/small/"/></a></p><p>"Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. 1).</p>Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61550/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61550/"><img alt="Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane" title="Wind-Tunnel Investigation at Low Speed of Sideslipping, Rolling, Yawing, and Pitching Characteristics for a Model of a 45 Degree Swept-Wing Fighter-Type Airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61550/small/"/></a></p><p>Report presenting an investigation in the stability tunnel at low speed to determine the rolling characteristics at combined angles of attack and sideslip for a model of a fighter-type airplane with a 45 degree sweptback wing. Testing was performed with the original vertical tail and a vertical tail with a 27 percent larger exposed area. Results regarding the static longitudinal stability, directional stability, and effect of the different tails are presented.</p>An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.012011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61551/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61551/"><img alt="An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01" title="An Experimental Investigation of the Flow Phenomena Over Bodies at High Angles of Attack at a Mach Number of 2.01" src="https://digital.library.unt.edu/ark:/67531/metadc61551/small/"/></a></p><p>Report presenting an investigation in the supersonic pressure tunnel at Mach number 2.01 to study the wake patterns in the lee of bodies at high angles of attack. The configurations tested consisted of two cylindrical body shapes, one circular and one elliptical in cross section, with a fineness-ratio-3.5 ogival nose and a fineness-ratio-6 conical nose. Results regarding vapor-screen photographs, wake characteristics, wake patterns, wake characteristics, and testing with transition strips are included.</p>Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61517/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61517/"><img alt="Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane" title="Wing-load measurements at supersonic speeds of the Douglas D-558-II research airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61517/small/"/></a></p><p>From Summary: "Flight measurements of the aerodynamic wing loads on the D-558-II airplane have been made in the Mach number range from 1.0 to 2.0. Nonlinear wing-panel characteristics occurred with variations in angle of attack. These nonlinear characteristics were apparent primarily at the lower supersonic speeds."</p>Statistical measurements of landing contact conditions of the Boeing B-47 airplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61528/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61528/"><img alt="Statistical measurements of landing contact conditions of the Boeing B-47 airplane" title="Statistical measurements of landing contact conditions of the Boeing B-47 airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61528/small/"/></a></p><p>Report presenting a determination of the landing contact conditions of the Boeing B-47 airplane using a specially built motion picture camera. A statistical analysis of the sinking speeds and horizontal speeds was carried out on the photographs.</p>Modified tubular combustor as high-temperature gas generators2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61530/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61530/"><img alt="Modified tubular combustor as high-temperature gas generators" title="Modified tubular combustor as high-temperature gas generators" src="https://digital.library.unt.edu/ark:/67531/metadc61530/small/"/></a></p><p>A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.</p>An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61421/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61421/"><img alt="An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface" title="An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface" src="https://digital.library.unt.edu/ark:/67531/metadc61421/small/"/></a></p><p>Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.</p>Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61424/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61424/"><img alt="Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings" title="Estimation of Incremental Pitching Moments Due to Trailing-Edge Flaps on Swept and Triangular Wings" src="https://digital.library.unt.edu/ark:/67531/metadc61424/small/"/></a></p><p>Report presenting a method by which incremental pitching moments can be estimated for swept and triangular wings with arbitrary types of trailing-edge high-lift flaps. Span-loading theory is combined with two-dimensional airfoil data adjusted for the effects of sweep. Application of the method is demonstrated for 58 cases covering various types of flaps on wings with a wide range of sweep, aspect ratio, and taper ratio.</p>Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61425/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61425/"><img alt="Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds" title="Aerodynamic heating of rocket-powered research vehicles at hypersonic speeds" src="https://digital.library.unt.edu/ark:/67531/metadc61425/small/"/></a></p><p>From Introduction: "The purpose of this paper is to present and discuss skin temperature measurements from two flight tests. Temperature measurements were obtained to a Mach number of 5.4 on the first flight and to a Mach number of 10.4 on the second flight."</p>Simplified procedures for estimating flap-control loads at supersonic speeds2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61520/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61520/"><img alt="Simplified procedures for estimating flap-control loads at supersonic speeds" title="Simplified procedures for estimating flap-control loads at supersonic speeds" src="https://digital.library.unt.edu/ark:/67531/metadc61520/small/"/></a></p><p>Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.</p>Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Transonic Mach Numbers 1.41 and 2.012011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61522/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61522/"><img alt="Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Transonic Mach Numbers 1.41 and 2.01" title="Force and Pressure Measurements on Several Canopy-Fuselage Configurations at Transonic Mach Numbers 1.41 and 2.01" src="https://digital.library.unt.edu/ark:/67531/metadc61522/small/"/></a></p><p>Report presenting an investigation on canopy pressures and canopy-fuselage forces and moments under conditions of combined pitch and sideslip. The canopy configurations tested varied in windshield shape (flat, vee, and round) and were tested at two Mach numbers and Reynolds numbers.</p>Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61523/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61523/"><img alt="Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines" title="Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines" src="https://digital.library.unt.edu/ark:/67531/metadc61523/small/"/></a></p><p>Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.</p>Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61544/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61544/"><img alt="Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds" title="Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds" src="https://digital.library.unt.edu/ark:/67531/metadc61544/small/"/></a></p><p>Report presenting chordwise pressure distributions measured over the left wing of the Convair XF-92A delta-wing airplane to determine the effect of lift on the wing characteristics at subsonic and transonic Mach numbers. Results regarding the chordwise pressure distributions, wing-section aerodynamic characteristics, spanwise distributions, and elevon-section loads are provided.</p>Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61546/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61546/"><img alt="Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination" title="Transonic wind-tunnel investigation of the effects of indentation on the wing loads of a 45 degree sweptback wing-body combination" src="https://digital.library.unt.edu/ark:/67531/metadc61546/small/"/></a></p><p>Report presenting the effects of an angle of incidence of 4 degrees and body indentation on wing loads of a sweptback wing-body combination at a range of Mach numbers. The wing had an aspect ratio of 4, taper ratio of 0.3, 45 degrees of sweepback of the quarter-chord line, and NACA 65A006 airfoil sections parallel to the plane of symmetry. Results regarding the effect of incidence and effect of body indentation are provided.</p>Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61547/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61547/"><img alt="Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane" title="Ditching investigation of a 1/25-scale model of a 255,000-pound transport airplane" src="https://digital.library.unt.edu/ark:/67531/metadc61547/small/"/></a></p><p>"An investigation was made of a 1/25-scale dynamically similar model of a 255,000-pound transport airplane in order to study its behavior when ditched. The model was free-launched from the Langley tank no. 2 monorail carriage into calm water. Various landing attitudes, flap settings, speeds, and configurations were investigated" (p. 1).</p>Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.982011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61442/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61442/"><img alt="Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98" title="Investigation of some wake vortex characteristics of an inclined ogive-cylinder body at Mach number 1.98" src="https://digital.library.unt.edu/ark:/67531/metadc61442/small/"/></a></p><p>Report presenting measurements of the pitot-pressure distributions in the flow field, pressure distributions over the body, and downwash distributions through shed vortices for an inclined body of revolution at a free-stream Mach number of 1.98. Results regarding the experimental pressure distributions and vortex positions, vortex strengths computed from experiment, comparisons of theoretical and experimental vortex paths, and comparisons of theoretical and experimental downwash distributions through the body vortices are provided.</p>Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.92011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61448/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61448/"><img alt="Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.9" title="Investigation of Equilibrium Temperatures and Average Laminar Heat-Transfer Coefficients for the Front Half of Swept Circular Cylinders at a Mach Number of 6.9" src="https://digital.library.unt.edu/ark:/67531/metadc61448/small/"/></a></p><p>Report presenting the average heat-transfer coefficients and equilibrium temperatures for the front half of an isothermal cylinder with a laminar boundary layer as determined by wind tunnel testing at Mach number 6.9 and a range of Reynolds numbers and sweep angles.</p>Preliminary performance data of several tail-pipe-cascade-type model thrust reversers2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61453/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61453/"><img alt="Preliminary performance data of several tail-pipe-cascade-type model thrust reversers" title="Preliminary performance data of several tail-pipe-cascade-type model thrust reversers" src="https://digital.library.unt.edu/ark:/67531/metadc61453/small/"/></a></p><p>Report presenting the reverse-thrust performance of several tail-pipe-cascade-type model thrust reversers over a range of exhaust-nozzle pressure ratios from 1.2 to 2.4. Both symmetrical and asymmetrical cascade blade shapes were investigated. Results regarding the performance of tail-pipe-cascade-type model thrust reversers having symmetrically shaped cascade blades and the performance of tail-pipe-cascade-type model thrust reversers having asymmetrically shaped cascade blades are provided.</p>Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61455/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61455/"><img alt="Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data" title="Theoretical Investigation of Laminar Heat Transfer on Yawed Infinite Cylinders in Supersonic Flow and a Comparison With Experimental Data" src="https://digital.library.unt.edu/ark:/67531/metadc61455/small/"/></a></p><p>Report presenting a theoretical method for calculating heat transfer in the laminar boundary layer on yawed infinite cylinders in compressible flow. The method can be applied to a cylinder of arbitrary cross section and arbitrary chordwise wall-temperature distribution. The variation in local heat transfer around the surface of the cylinder was found to have little functional dependence on yaw angle or wall temperature.</p>Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61465/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61465/"><img alt="Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance" title="Experimental investigation of a transonic compressor rotor with a 1.5-inch chord length and an aspect ratio of 3.0 2: blade-element performance" src="https://digital.library.unt.edu/ark:/67531/metadc61465/small/"/></a></p><p>Report presenting a transonic compressor rotor with double-circular-arc blade sections, which were designed and tested to investigate the aerodynamic effects of using a short blade chord and a high aspect ratio. The report presents the blade-element performance and performance analysis.</p>Some Effects of Fluid in Pylon-Mounted Tanks on Flutter2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61466/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61466/"><img alt="Some Effects of Fluid in Pylon-Mounted Tanks on Flutter" title="Some Effects of Fluid in Pylon-Mounted Tanks on Flutter" src="https://digital.library.unt.edu/ark:/67531/metadc61466/small/"/></a></p><p>Report presenting fluid-dynamics studies of a tank of fineness ratio 7.0 which was pylon mounted on a simplified two-dimensional flutter model in order to determine the effects of the fluid on flutter. The flutter speed was determined for three cases: with various amounts of water in the tank, with weights with the same mass and moment of inertia as the fluid considered to be a frozen solid, and with weights with the same mass and moment of inertia as the actual fluid. Results regarding the flutter speed, effects of inertia on flutter, and amplitude of flutter are provided.</p>The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61469/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61469/"><img alt="The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers" title="The Unsteady Normal-Force Characteristics of Selected NACA Profiles at High Subsonic Mach Numbers" src="https://digital.library.unt.edu/ark:/67531/metadc61469/small/"/></a></p><p>Report presenting a wind-tunnel investigation at subsonic Mach numbers up to 0.9 to measure the root-mean-square variation of the normal forces on 27 NACA airfoil sections. The effects of thickness-chord ratio, camber, location of minimum pressure, and leading-edge radius were investigated.</p>Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61493/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61493/"><img alt="Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades" title="Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades" src="https://digital.library.unt.edu/ark:/67531/metadc61493/small/"/></a></p><p>Report presenting an investigation of the stress distribution in the roots of the first three stages of the J6S axial-flow compressor in order to explain root failures experienced in service. Root failures were producible in the lab when high vibratory stresses were combined with simulated centrifugal loads. Results regarding fatigue tests on the original J6S blade roots and on two redesigned blade roots as well as a comparison of the different root designs are provided.</p>Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.62011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61495/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61495/"><img alt="Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6" title="Collection and summary of flap-type-aileron rolling-effectiveness data at zero lift as determined by rocket-powered model tests at Mach numbers between 0.6 and 1.6" src="https://digital.library.unt.edu/ark:/67531/metadc61495/small/"/></a></p><p>Report presenting a collection and summary of the wing-aileron rolling-effectiveness data obtained as part of an investigation of lateral control using rocket-powered test vehicles in free flight over a range of Mach numbers. Some effects of trailing-edge angle, aileron-chord ratio, aileron span and location, aspect ratio, wing sweepback, and wing-tail interference are provided.</p>Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61497/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61497/"><img alt="Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees" title="Flight Measurements of Horizontal-Tail Loads on the Bell X-5 Research Airplane at a Sweep Angle of 58.7 Degrees" src="https://digital.library.unt.edu/ark:/67531/metadc61497/small/"/></a></p><p>A flight investigation was made at altitudes of 40,000, 25,000 and 15,000 feet to determine the horizontal-tail loads of the Bell X-5 research airplane at a sweep angle of 58.7 deg over the lift range of the airplane for Mach numbers from 0.61 to 1.00. The horizontal-tail loads were found to be nonlinear with lift throughout the lift ranges tested at all Mach numbers except at a Mach number of 1.00. The balancing tail loads reflected the changes which occur in the wing characteristics with increasing angle of attack. The nonlinearities were, in general, more pronounced at the higher angles of attack near the pitch-up where the balancing tail loads indicate that the wing-fuselage combination becomes unstable.</p>Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow2011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61486/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61486/"><img alt="Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow" title="Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow" src="https://digital.library.unt.edu/ark:/67531/metadc61486/small/"/></a></p><p>Report presenting a theory of reduction of convective heat transfer to a surface in supersonic flow by periodically imposing a large-scale vortical motion on the boundary layer and an experimental investigation of that theory. Results regarding the pulsating flow phenomena, heat-transfer characteristics, and aerodynamic characteristics are provided.</p>Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers From 0.6 to 1.4 of a Wing-Body-Tail Combination Having an Unswept Wing of Aspect Ratio 32011-11-17T22:13:23-06:00https://digital.library.unt.edu/ark:/67531/metadc61489/<p><a href="https://digital.library.unt.edu/ark:/67531/metadc61489/"><img alt="Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers From 0.6 to 1.4 of a Wing-Body-Tail Combination Having an Unswept Wing of Aspect Ratio 3" title="Effects of Taper Ratio on the Longitudinal Characteristics at Mach Numbers From 0.6 to 1.4 of a Wing-Body-Tail Combination Having an Unswept Wing of Aspect Ratio 3" src="https://digital.library.unt.edu/ark:/67531/metadc61489/small/"/></a></p><p>Report presenting the results of a wind-tunnel investigation to determine the effects of a variation in wing taper ratio on the longitudinal characteristics of a wing-body combination at a variety of Mach numbers. The wings had an aspect ratio of 3, an unswept midchord line, and an NACA 64A003 profile. Results regarding the lift and pitching-moment characteristics and drag characteristics are provided.</p>