National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results
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- Investigation of Wingless Missile Configurations with Folding Controls and Low-Aspect-Ratio Stabilizing Surfaces
- 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.
- Measurements of the Buffeting Loads on the Wing and Horizontal Tail of a 1/4-Scale Model of the X-1E Airplane
- "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).
- Stability Investigation of a Blunt Cone and a Blunt Cylinder With a Square Base at Mach Numbers From 0.64 to 2.14
- 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.
- Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet
- 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.
- Effect of Spike-Tip and Cowl-Lip Blunting on Inlet Performance of a Mach 3.0 External-Compression Inlet
- 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.
- 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
- 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.
- Experimental Study of Ballistic-Missile Base Heating with Operating Rocket
- "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).
- Investigation of Inlet Control Parameters for an External-Internal-Compression Inlet From Mach 2.1 to 3.0
- "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).
- Analysis of pressure data obtained at transonic speeds on a thin low-aspect-ratio cambered delta wing-body combination
- 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."
- Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-Cylinder-Flare Configuration at Mach Numbers Up to 9.89
- Skin temperature and surface pressure of blunted cone-cylinder-flare configuration free flight test vehicle to hypersonic speeds.
- Large-scale wind-tunnel tests of a jet-transport-type model with leading- and trailing-edge high-lift devices
- 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."
- 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
- 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.
- Some Notes on the Probable Damage to an Intercontinental-Ballistic-Missile Warhead Following Puncture of the Heat Shield
- 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.
- Combustor performance with various hydrogen-oxygen injection methods in a 200-pound-thrust rocket engine
- 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.
- Off-Design Performance of Divergent Ejectors
- 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.
- Off-Design Performance of Divergent Ejectors
- "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).
- 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
- 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.
- Screaming tendency of the gaseous-hydrogen - liquid-oxygen propellant combination
- 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.
- Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
- 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.
- Use of Highly Reactive Chemical Additives to Improve Afterburner Performance at Altitude
- 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.
- Aerodynamic characteristics of the X-15/B-52 combination
- Report presenting an investigation to determine the carry loads and mutual aerodynamic interference effects from high-speed wind-tunnel tests and the drop characteristics of the X-15 through the B-52 flow field from low-speed dynamic-model drop tests and six-degree-of-freedom calculations. The X-15 installation was found to increase drag at cruise conditions by approximately 15 percent.
- Boundary-Layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6
- "Measurements are presented for pressure gradients induced by a laminar boundary layer on a flat plate in air at a Mach number of 9.6 and for the drag of thin wings at a Mach number of about 6.8 and zero angle of attack. The pressure measurements at a Mach number of 9.6 were made in the presence of substantial heat transfer from the boundary layer to the plate surface. The measured pressure distribution o the surface of the plate was predicted with good accuracy by a modification to insulated-plate displacement theory which allows for the effect of the heat transfer and temperature gradient along the surface on the boundary-layer displacement thickness" (p. 1).
- Forty-Fourth Annual Report of the National Advisory Committee for Aeronautics Administrative Report Including Technical Reports Nos. 1342 to 1392
- "In accordance with act of Congress, approved March 3, 1915, as amended (U.S.C., title 50, .sw 151), which established the National Advisory Committee for Aeronautics, the Committee submits its Forty-fourth Annual Report for the fiscal year 1958. This is the Committee's final report to the Congress. The National Aeronautics and Space Act of 1958 (Public Law 85-568) provides in section 301 that the NACA "shall cease to exist" and "all functions, powers, duties, and obligations, and all real and personal property, personnel (other than members of the Committee), funds, and records of the NACA shall be transferred to the National Aeronautics and Space Administration" (p. ix).
- 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
- 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.
- 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
- 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.
- Some Research on the Lift and Stability of Wing-Body Combinations
- 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.
- Spin Tunnel Investigation of a 1/30 Scale Model of the North American A-5A Airplane
- "An investigation has been made in the Langley spin tunnel to determine the erect and inverted spin and recovery characteristics of a 1/30-scale dynamic model of the North American A-5A airplane. Tests were made for the basic flight design loading with the center of gravity at 30-percent mean aerodynamic chord and also for a forward position and a rearward position with the center of gravity at 26-percent and 40-percent mean aerodynamic chord, respectively. Tests were also made to determine the effect of full external wing tanks on both wings, and of an asymmetrical condition when only one full tank is carried" (p. 1).
- Spin-Tunnel Investigation of a 1/28-Scale Model of a Subsonic Attack Airplane
- "An investigation has been made of a 1/28-scale model of the Grumman A-6A airplane in the Langley spin tunnel. The erect spin and recovery characteristics of the model were determined for the flight design gross weight loading and for a loading with full internal fuel and empty external wing fuel tanks. The effects of extending slats and deflecting flaps were investigated" (p. 1).
- Smoking Characteristics of Various Fuels as Determined by Open-Cup and Laboratory-Burner Smoke Tests
- Report discussing tests in a combustion chamber to obtain smoking characteristics data on a variety of hydrocarbon fuels. Details about the smoking tendencies and burning rates of the fuels in uncontrolled and controlled tests are provided.
- The Aerodynamic Forces on Airship Hulls
- The new method for making computations in connection with the study of rigid airships, which was used in the investigation of Navy's ZR-1 by the special subcommittee of the National Advisory Committee for Aeronautics appointed for this purpose is presented. The general theory of the air forces on airship hulls of the type mentioned is described and an attempt was made to develop the results from the very fundamentals of mechanics.
- Applications of Modern Hydrodynamics to Aeronautics Part 1: Fundamental Concepts and the Most Important Theorems. Part 2: Applications
- A discussion of the principles of hydrodynamics of nonviscous fluids in the case of motion of solid bodies in a fluid is presented. Formulae are derived to demonstrate the transition from the fluid surface to a corresponding 'control surface'. The external forces are compounded of the fluid pressures on the control surface and the forces which are exercised on the fluid by any solid bodies which may be inside of the control surfaces.
- Flow and Drag Formulas for Simple Quadrics
- The pressure distribution and resistance found by theory and experiment for simple quadrics fixed in an infinite uniform stream of practically incompressible fluid are calculated. The experimental values pertain to air and some liquids, especially water; the theoretical refer sometimes to perfect, again to viscid fluids. Formulas for the velocity at all points of the flow field are given. Pressure and pressure drag are discussed for a sphere, a round cylinder, the elliptic cylinder, the prolate and oblate spheroid, and the circular disk. The velocity and pressure in an oblique flow are examined.
- Flow and Force Equations for a Body Revolving in a Fluid
- A general method for finding the steady flow velocity relative to a body in plane curvilinear motion, whence the pressure is found by Bernoulli's energy principle is described. Integration of the pressure supplies basic formulas for the zonal forces and moments on the revolving body. The application of the steady flow method for calculating the velocity and pressure at all points of the flow inside and outside an ellipsoid and some of its limiting forms is presented and graphs those quantities for the latter forms.
- Graphic Construction of Joukowski Wings
- Memorandum presenting a description and formulas that can be used to plot the cross-sectional outline of a Joukowski wing.
- The Minimum Induced Drag of Aerofoils
- Equations are derived to demonstrate which distribution of lifting elements result in a minimum amount of aerodynamic drag. The lifting elements were arranged (1) in one line, (2) parallel lying in a transverse plane, and (3) in any direction in a transverse plane. It was shown that the distribution of lift which causes the least drag is reduced to the solution of the problem for systems of airfoils which are situated in a plane perpendicular to the direction of flight.
- The Theory of the Pitot and Venturi Tubes, Part 2
- Report discussing several aspects of pitot and venturi tubes, including the energy equation for steady adiabatic flow, introduction of mean speed into the energy equation, isentropic flow of an ideal gas, the theory of the pitot tube, and the theory of the venturi meter.