Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- A Theoretical Analysis of the Effects of Fuel Motion on Airplane Dynamics
- Wind-Tunnel Investigation of the Low-Speed Static Stability and Control Characteristics of a Model of the Bell MX-776 (RASCAL) in Combined Angle of Attack and Sideslip
- Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal
- Investigation in the Ames Supersonic Free-Flight Wind Tunnel of the Static Longitudinal Stability of the Hermes A-3B Missile at a Mach Number of 5.0
- Method for Calculation of Laminar Heat Transfer in Air Flow Around Cylinders of Arbitrary Cross Section (Including Large Temperature Differences and Transpiration Cooling)
- A Wind-Tunnel Investigation to Determine the Effect of Various Head Designs on the Aerodynamic Characteristics in Pitch of the Army Ordnance Corps T205 3.5-Inch Heat Rocket
- Investigation of Spinning and Tumbling Characteristics of a 1/20-Scale Model of the Consolidated Vultee XFY-1 Airplane in the Free-Spinning Tunnel, TED No. NACA DE 370
- Preliminary Results Obtained from Flight Test of a 1/7-Scale Rocket-Powered Model of the Grumman XF10F Airplane Configuration in the Swept-Wing Condition, TED No. NACA DE 354
- Effect of Various Blade Modifications on Performance of a 16-Stage High-Pressure-Ratio Axial-Flow Compressor 1 - Effect on Over-All Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-Blade Angles 3 Degrees
- Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 2 - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 Degrees
- Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 5 - Effect on Over-All Performance Characteristics of a 20-Percent Reduction in Solidity of the Fourteenth Through Sixteenth Stage Rotors
- Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 3 - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages
- Effect of Rotor- and Stator-Blade Modifications on Surge Performance of an 11-Stage Axial-Flow Compressor 1 - Original Production Compressor of XJ40-WE-6 Engine
- Detailed Computational Procedure for Design of Cascade Blades With Prescribed Velocity Distributions in Compressible Potential Flows
- Ditching Investigation of a 1/12-Scale Model of the Douglas F3D-2 Airplane, TED No. NACA DE 381
- The Effect of an Operating Propeller on the Aerodynamic Characteristics of a 1/10-Scale Model of the Lockheed XFV-1 Airplane at High Subsonic Speeds (TED No. NACA DE-377)
- Concerning the Flow About Ring-Shaped Cowlings Part 9: The Influence of Oblique Oncoming Flow on the Incremental Velocities and Air Forces at the Front Part of Circular Cowls
- On Rotational Conical Flow
- Amplitude of Supersonic Diffuser Flow Pulsations
- Wind-Tunnel Investigation of the Static Longitudinal Stability Characteristics of a 0.15-Scale Model of the Hermes A-1E2 Missile at High Subsonic Mach Numbers
- An Approximate Method of Calculating the Deformations of Wings Having Swept, M or W, A, and Swept-Tip Plan Forms
- Some Experiences Regarding the Nonlinearity of Hot Wires
- Small-Scale Transonic Investigation of the Effects of Partial-Span Leading-Edge Camber on the Aerodynamic Characteristics of a 50 Degree 38' Sweptback Wing of Aspect Ratio 2.98
- Thirty-Seventh Annual Report of the National Advisory Committee for Aeronautics: Administrative Report Including Technical Report Nos. 1003 to 1058
- Time-History Data of Maneuvers Performed by an F-86A Airplane During Squadron Operational Training
- A method of calibrating airspeed installations on airplanes at transonic and supersonic speeds by the use of accelerometer and attitude-angle measurements
- Analysis of V-g records from the Grumman F8F-2 airplane
- Performance Characteristics at Mach Numbers to 2.0 of Various Types of Side Inlets Mounted on Fuselage of Proposed Supersonic Airplane 2: Inlets Utilizing Half of a Conical Spike
- Preliminary Investigation of the Low-Amplitude Damping in Pitch of Tailless Delta- and Swept-Wing Configurations at Mach Numbers From 0.7 to 1.35
- Preliminary Results of Horizontal-Tail Load Measurements of the Bell X-5 Research Airplane
- Preliminary Tank Tests of Some Hydro-Ski-Wheel Combinations in the Planing Condition
- An Experimental Investigation of the Base Pressure Characteristics of Nonlifting Bodies of Revolution at Mach Numbers From 2.73 to 4.98
- Experimental Investigation of the Effects of Vortex Generators on the Maximum Lift of a 6-Percent-Thick Symmetrical Circular-Arc Airfoil Section
- Experimental Investigation of Internal Flow Characteristics of Forward Underslung Fuselage Scoops With Unswept Entrances at Mach Numbers of 1.41 to 1.96
- Some Low-Speed Studies of the Effects of Wing Location on Wing-Deformation-Body-Freedom Flutter
- Rocket-Model Investigation to Determine the Force and Hinge-Moment Characteristics of a Half-Delta Tip Control on a 59 Degree Sweptback Delta Wing Between Mach Numbers of 0.55 and 1.43
- Rocket-Model Investigation of the Rolling Effectiveness of a Fighter-Type Wing-Control Configuration at Mach Numbers From 0.6 to 1.5
- Preliminary Investigation of the Effects of Inlet Asymmetry on the Performance of Converging-Diverging Diffusers at Transonic Speeds
- A Preliminary Low-Speed Wind-Tunnel Investigation of a Thin Delta Wing Equipped With a Double and a Single Slotted Flap
- A Preliminary Investigation of the Static and Dynamic Longitudinal Stability of a Grunberg Hydrofoil System
- Time-History Data of Maneuvers Performed by McDonnell F2H-2 Airplane During Squadron Operational Training
- Total-Pressure and Schlieren Studies of the Wakes of Various Canard Control Surfaces Mounted on a Missile Body at a Mach Number of 1.93
- Total-Pressure Recovery of a Circular Underslung Inlet With Three Different Nose Shapes at a Mach Number of 1.42
- Transonic Drag Characteristics and Pressure Distribution on the Body of a Wing-Body Combination Consisting of a Body of Revolution of Fineness Ratio 12 and a Wing Having Sweepback of 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Sections
- Transonic Flight Tests to Compare the Zero-Lift Drags of 45 Degree Sweptback Wings of Aspect Ratio 3.55 and 6.0 With and Without Nacelles at the Wing Tips
- Transonic Flight Tests to Determine Zero-Lift Drag and Pressure Recovery of Nacelles Located at the Wing Tips on a 45 Degree Sweptback Wing and Body Combination
- Use of an Aerodynamically Pulsed All-Movable Horizontal Tail to Obtain Longitudinal Characteristics of Rocket-Powered Models in Free Flight and Some Initial Results From an Arrow-Wing-Body-Tail Configuration
- A Transonic Wind-Tunnel Investigation of the Aerodynamic Characteristics of Three 4-Percent-Thick Wings of Sweepback Angles 10.8 Degrees, 35 Degrees, and 47 Degrees, Aspect Ratio 3.5, and Taper Ratio 0.2 in Combination With a Body
- Pressure Distributions on Bodies of Revolution at Subsonic and Transonic Speeds
- Pressure Distributions at Mach Numbers From 0.6 to 1.9 Measured in Free Flight on a Parabolic Body of Revolution With Sharply Convergent Afterbody