Search
Search U.S. government technical reports digitized or harvested by TRAIL.
Keyword Search
14045 results returnedSearch results
- Investigation of the Aerodynamic Effects of an External Store in Combination With 60 Degree Delta and Low-Aspect-Ratio Tapered Wings at a Mach Number of 1.9
- An Investigation of Four Wings of Square Plan Form at a Mach Number of 6.86 in the Langley 11-Inch Hypersonic Tunnel
- An Investigation of the Longitudinal Characteristics of the X-3 Configuration With Wing and Horizontal Tail Surfaces of Aspect Ratio 3.0 by Means of Rocket-Propelled Models: Results at High Lift Coefficients
- Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the Douglas X-3 Airplane
- Flight Performance of a Twin-Engine Supersonic Ram Jet From 2,300 to 67,200 Feet Altitude
- Free-Flight Investigation to Determine Force and Hinge-Moment Characteristics at Zero Angle of Attack of a 60 Degrees Sweptback Half-Delta Tip Control on a 60 Degrees Sweptback Delta Wing at Mach Numbers Between 0.68 and 1.44
- Free-Jet Tests of a 6.5-Inch-Diameter Ram-Jet Engine at Mach Numbers 1.81 and 2.00
- An Investigation at Transonic Speeds of the Effects of Control Chord and Span on the Control Characteristics of a Tapered Wedge-Type Wing of Aspect Ratio 2.5: Transonic-Bump Method
- Investigation at Mach Number 1.88 of Half of a Conical-Spike Diffuser Mounted as a Side Inlet With Boundary-Layer Control
- Wind-Tunnel Investigation at Low Speed of the Effects of Symmetrical Deflection of Half-Delta Tip Controls on the Damping in Roll and Yawing Moment Due to Rolling of a Triangular-Wing Model
- A Comparison of Theory and Experiment for High-Speed Free-Molecule Flow
- The aerodynamic behavior of a harmonically oscillating finite sweptback wing in supersonic flow
- Air forces and moments on triangular and related wings with subsonic leading edges oscillating in supersonic potential flow
- An analysis of an x-ray absorption method for measurement of high gas temperatures
- Development of Auxiliary Cyclotron Equipment for Using Tritium as Bombarding Particles in a Cyclotron
- Contributions to the theory of the spreading of a free jet issuing from a nozzle
- Approximate method of integration of laminar boundary layer in incompressible fluid
- Gas flow with straight transition line
- Experiments on transonic flow around wedges
- Sound from a two-blade propeller at supersonic tip speeds
- Mechanism of start and development of aircraft crash fires
- Electrical Pressure Integrator
- Abnormal Grain Growth in S-816 Alloy
- Experimental investigation of air-flow uniformity and pressure level on wire cloth for transpiration-cooling applications
- Error in airspeed measurement due to static-pressure field ahead of an open-nose air-inlet model at transonic speeds
- Experimental investigation of flow through three highly loaded inlet guide vanes having different spanwise circulation gradients
- Flutter of a 60©� delta wing (NACA 65A003 airfoil) encountered at supersonic speeds during the flight test of a rocket-propelled model
- Miscellaneous directional-stability data for several airplane-like configurations from rocket-model tests at transonic speeds
- Preliminary investigation of the effects of heat transfer on boundary-layer transition on a parabolic body of revolution (NACA RM-10) at a Mach number of 1.61
- 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©�
- Heat transfer and skin friction for turbulent boundary layers on heated or cooled surfaces at high speeds
- Investigation of the variation with Reynolds number of the base, wave, and skin-friction drag of a parabolic body of revolution (NACA RM-10) at Mach numbers of 1.62, 1.93, and 2.41 in the Langley 9-inch supersonic tunnel
- 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
- Low-Speed Wind-Tunnel Investigation of the Drag of a Lockheed F-94C Airplane (A.F. No. 50-956)
- Free-Flight-Tunnel Investigation of the Dynamic Stability and Control Characteristics of a Chance Vought F7U-3 Airplane in Towed Flight
- As Investigation at Mach Numbers of 1.41 and 2.01 of the Aerodynamic Characteristics of an 0.025-scale Model of the MX-1712
- An Investigation of the Effect of the WADC 30,000-Horsepower Whirl Rig Upon the Static Characteristics of a Propeller
- Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. IV - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages
- A Photographic Study of Freezing of Water Droplets Falling Freely in Air
- Preliminary Survey of Icing Conditions Measured During Routine Transcontinental Airline Operation
- Impingement of Water Droplets on an NACA 65(sub 1) -212 Airfoil at an Angle of Attack of 4 Deg
- The Calculated and Measured Performance Characteristics of a Heated-Wire Liquid-Water-Content Meter for Measuring Icing Severity
- Experimental Investigation of Average Heat-Transfer and Friction Coefficients for Air Flowing in Circular Tubes Having Square-Thread-Type Roughness
- Experimental and theoretical determination of thermal stresses in a flat plate
- Flow characteristics over a lifting wedge of finite aspect ratio with attached and detached shock waves at a Mach number of 1.40
- Investigation of hydrocarbon ignition
- A blade-element analysis for lifting rotors that is applicable for large inflow and blade angles and any reasonable blade geometry
- Landing characteristics in waves of three dynamic models of flying boats
- Effect of compressibility on the flow past a two-dimensional bump
- Effect of changing passage configuration on internal-flow characteristics of a 48-inch centrifugal compressor