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- The Wave Drag of Arbitrary Configurations in Linearized Flow as Determined by Areas and Forces in Oblique Planes
- Vibratory-Stress Investigation of Six- and Eight-Blade-Dual-Rotating Propellers Operating at Zero Advance
- Velocity Distributions Measured in the Slipstream of Eight-Blade and Six-Blade Dual-Rotating Propellers at Zero Advance
- 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
- Wind-Tunnel Investigation at Transonic Speeds of a Jet Control on an 80 Degree Delta-Wing Missile
- Transonic Wind-Tunnel Investigation of the Aerodynamic Loading Characteristics of a 60 Degree Delta Wing in the Presence of a Body With and Without Indentation
- Transonic Wind-Tunnel Investigation of Effects of Windshield Shape and Canopy Location on the Aerodynamic Characteristics of Canopy-Body Combinations
- Transonic Longitudinal Aerodynamic Effects of Sweeping Up the Rear of the Fuselage of a Rocket-Propelled Airplane Model Having No Horizontal Tail
- An Analysis of the Transonic and Supersonic Performance of Several Fixed-Geometry Air Inlets
- Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds
- Preliminary Flight-Determined Pressure Distributions Over the Wing of the Douglas X-3 Research Airplane at Subsonic and Transonic Mach Numbers
- Calculated Heats of Formation and Combustion of Boron Compounds (Boron, Hydrogen, Carbon, Silicon)
- The Effect of Wing Fences on the Longitudinal Characteristics at High Subsonic Speeds of a Wing-Fuselage-Tail Combination Having a Wing With 40 Degrees of Sweepback and NACA Four-Digit Thickness Distribution
- Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular Wing and Body Combinations at a Mach Number of 1.62
- Wind-Tunnel Investigation of the Static Longitudinal and Lateral Stability of the Bell X-1A at Supersonic Speeds
- Wind-Tunnel Measurements of the Dynamic Cross Derivative (Rolling Moment Due to Yawing Velocity and to Acceleration in Sideslip) of the Douglas D-558-II Airplane and Its Components at Supersonic Speeds Including Description of the Technique
- Tests of Aerodynamically Heated Multiweb Wing Structures in a Free Jet at Mach Number 2: Two Aluminum-Alloy Models of 20-Inch Chord With 0.064- and 0.081-Inch-Thick Skin
- The Effect of Base Bleed on the Base Pressure, Lift, Drag, and Pitching Moment of a 10-Percent-Thick Blunt-Base Airfoil at a Mach Number of 2.72
- Effects of Some Leading-Edge Modifications, Section and Plan-Form Variations, and Vertical Position on Low-Lift Wing Drag at Transonic and Supersonic Speeds
- 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
- Effects of a Detached Tab on the Hinge-Moment and Effectiveness Characteristics of an Unswept Trailing-Edge Control on a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
- Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor
- Effect of Reduced Stator-Blade Trailing-Edge Thickness on Over-All Performance of a Transonic Turbine
- Effect of Several Modifications to Center Body and Cowling on Supercritical Performance of a Supersonic Inlet at Mach Number of 2.02
- Effects of Boundary-Layer Separation on Normal Force and Center of Pressure of a Cone-Cylinder Model With a Large Base Flare at Mach Numbers From 3.00 to 6.28
- Effects of Combining Auxiliary Bleed With Ejector Pumping on the Power Requirements and Test-Section Flow of an 8-Inch by 8-Inch Slotted Tunnel
- Experimental Flutter Results for Cantilever-Wing Models at Mach Numbers Up to 3.0
- Drag Investigation of a Swept-Wing Fighter-Airplane Model Incorporating Two Drag-Rise-Reducing Fuselage Revisions
- A Drop Test for the Evaluation of the Impact Strength of Cermets
- A Dynamic-Model Study of the Effect of Added Weights and Other Structural Variations on the Blade Bending Strains of an Experimental Two-Blade Jet-Driven Helicopter in Hovering and Forward Flight
- Effect of an All-Movable Wing-Tip Control on the Longitudinal Stability of 60 Degree Sweptback-Wing-Indented-Body Configuration Equipped With Fences at Transonic Speeds
- High-Altitude Performance of an Experimental Turbojet Combustor Having Variable Primary-Air Admission
- Aircraft-Fuel-Tank Design for Liquid Hydrogen
- Correlation of Vibratory Root Failures and Stress Distribution in J65 Compressor Blades
- A Correlation of Two-Dimensional Data on Lift Coefficient Available With Blowing-, Suction-, Slotted-, and Plain-Flap High-Lift Devices
- Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey
- Aerodynamic Characteristics of a 1/4-Scale Model of the Duct System for the General Electric P-1 Nuclear Powerplant for Aircraft
- Acceleration Characteristics of a Turbojet Engine With Variable-Position Inlet Guide Vanes
- Aerodynamic Loading Characteristics in Sideslip of a 45 Degree Sweptback Wing With and Without a Fence at High Subsonic Speeds
- An Investigation of Drains Discharging Liquid Into Subsonic and Transonic Streams
- An Investigation of Jet Effects on Adjacent Surfaces
- Investigation of Interference Lift, Drag, and Pitching Moment of a Series of Triangular-Wing and Body Combinations at a Mach Number of 1.94
- An Investigation of Loads on Ailerons at Transonic Speeds
- An Investigation of the Effects of Rapid Skin Heating on Box Beams Loaded in Bending
- A Flight Investigation at Transonic Speeds of a Model Having a Triangular Wing of Aspect Ratio 4
- Flight Measurements at Transonic Speeds of the Buffeting Characteristics of the XF-92A Delta-Wing Research Airplane
- Flight Investigation of the Supersonic Area Rule for a Straight Wing-Body Configuration at Mach Numbers Between 0.8 and 1.5
- Flight Investigation of the Effect of Underwing Propulsive Jets on the Lift, Drag, and Longitudinal Stability of a Delta-Wing Configuration at Mach Numbers From 1.23 to 1.62
- Flight Investigation of a Roll-Stabilized Ram-Jet Test Vehicle Over a Mach Number Range of 2.3 to 2.7
- Flight Investigation at Supersonic Mach Numbers of an Automatic Acceleration Control Missile in Which Rate Damping Is Obtained From a Linear Accelerometer Placed Ahead of the Missile Center of Gravity