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- Pressure Distribution and Aerodynamic Coefficients Associated With Heat Addition to Supersonic Air Stream Adjacent to Two-Dimensional Supersonic Wing
- Pressure Measurements on an Ogive-Cylinder Body at Mach Number 4.04
- Propeller Induced Angles of Attack and Section Angles of Attack for the NACA 10-(3)(066)-03, 10-(3)(049)-03, 10-(3)(090)-03, 10-(5)(066)-03, and 10-(0)(066)-03 Propellers
- Propeller Lift and Thrust Distribution From Wake Surveys of Stagnation Conditions
- Some Effects of Aeroelasticity at Mach Numbers From 0.7 to 1.6 on the Rolling Effectiveness of Thin Flat-Plate Delta Wings Having 45 Degree Swept Leading Edges and Full-Span Constant-Chord Ailerons
- Some Effects of Spoiler Height, Wing Flexibility, and Wing Thickness on Rolling Effectiveness and Drag of Unswept Wings at Mach Numbers Between 0.4 and 1.7
- Theoretical Calculation of the Effect of the Fuselage on the Spanwise Lift Distribution on a Wing
- Theoretical Damping in Roll and Rolling Moment Due to Differential Wing Incidence for Slender Cruciform Wings and Wing-Body Combinations
- Time Histories of Maneuvers Performed With an F-86A Airplane During Squadron Operations
- The Use of the Rolled-Up Vortex Concept for Predicting Wing-Tail Interference and Comparison With Experiment at Mach Number of 1.62 for a Series of Missile Configurations Having Tandem Cruciform Lifting Surfaces
- The Use of Area Suction for the Purpose of Delaying Separation of Air Flow at the Leading Edge of a 63 Degree Swept-Back Wing: Effects of Controlling the Chordwise Distribution of Suction Air Velocities
- Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds
- Wind-Tunnel Investigation at High and Low Subsonic Mach Numbers of a Thin Sweptback Wing Having an Airfoil Section Designed for High Maximum Lift
- Wind-Tunnel Investigation at High Subsonic Speeds of Spoilers of Large Projection on an NACA 65A006 Wing With Quarter-Chord Line Swept Back 32.6 Degrees
- A Wind-Tunnel Investigation at Low Speeds of the Aerodynamic Characteristics of Various Spoiler Configurations on a Thin 60 Degrees Delta Wing
- Wind-Tunnel Investigation of the Low-Speed Static and Rotary Stability Derivatives of a 0.13-Scale Model of the Douglas D-558-II Airplane in the Landing Configuration
- A Transonic Investigation of the Aerodynamic Characteristics of Plate- and Bell- Type Outlets for Auxiliary Air
- Investigation of Effective Thermal Conductivities of Powders
- Wind-Tunnel Investigation of the Static Lateral Stability Characteristics of Wing-Fuselage Combinations at High Subsonic Speeds: Sweep Series
- A Theoretical Investigation of the Effect of a Target Seeker Sensitive to Pitch Attitude on the Dynamic Stability and Response Characteristics of a Supersonic Canard Missile Configuration
- Thrust Loading of the NACA 3-(3)(05)-05 Eight-Blade Dual-Rotating Propeller as Determined From Wake Surveys
- First Landing of Bell X-2 Research Airplane
- The Effect of Surface Roughness on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers
- Evaluation of End- and Radial-Burning Solid Fuels in Ram Jets Mounted in a Free Jet at Mach Numbers of 2.0, 2.2, and 2.3
- Effects of Chord Discontinuities and Chordwise Fences on Low-Speed Static Longitudinal Stability of an Airplane Model Having a 35 Degree Sweptback Wing
- The Effects of Camber and Leading-Edge-Flap Deflection on the Pressure Pulsations on Thin Rigid Airfoils at Transonic Speeds
- The Effect of Entrance Mach Number and Lip Shape on the Subsonic Characteristics of a Scoop-Type-Air-Induction System for a Supersonic Airplane
- Effect of Fuselage Interference on the Damping in Roll of Delta Wings of Aspect Ratio 4 in the Mach Number Range Between 0.6 and 1.6 as Determined With Rocket Propelled Vehicles
- Effect of Fuel-Air Distribution on Performance of a 16-Inch Ram-Jet Engine
- Stability and Control Flight Tests of a 0.13-Scale Model of the Consolidated-Vultee XFY-1 Airplane in Take-Offs, Landings, and Hovering Flight: TED No. NACA DE 368
- Comparison of Locked-Rotor and Windmilling Drag Characteristics of an Axial-Flow-Compressor Type Turbojet Engine
- The Calculation of Certain Static Aeroelastic Phenomena of Wings With Tip Tanks or Boom-Mounted Lifting Surfaces
- Calculation of Internal Pressures in the Fuel Tube of a Nuclear Reactor
- Calibration of the Slotted Test Section of the Langley 8-Foot Transonic Tunnel and Preliminary Experimental Investigation of Boundary-Reflected Disturbances
- Axial-Slot Air Admission for Controlling Performance of a One-Quarter-Annual Turbojet Combustor and Comparison With Complete Engine
- Aerodynamic Characteristics of Two Delta Wings at Mach Number 4.04 and Correlations of Lift and Minimum-Drag Data for Delta Wings at Mach Numbers From 1.62 to 6.9
- Aerodynamic Loading Characteristics of a Wing-Fuselage Combination Having a Wing of 45 Degrees Sweepback Measured in the Langley 8-Foot Transonic Tunnel
- Aerodynamic Load Measurements Over a Leading-Edge Slat on a 40 Degree Sweptback Wing at Mach Numbers From 0.10 to 0.91
- Aeronautical Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination and the Fuselage Alone Obtained in the Langley 8-Foot Transonic Tunnel
- Longitudinal Stability, Trim, and Drag Characteristics of a Rocket-Propelled Model of an Airplane Configuration Having a 45 Degree Sweptback Wing and an Unswept Horizontal Tail
- Investigation of Interference, Lift, Drag, and Pitching Moment of a Series of Rectangular Wing and Body Combinations at Mach Numbers of 1.62, 1.93,and 2.41
- An Investigation of Longitudinal Control Characteristics of a Wing-Tip Control Surface on a Sweptback Wing at Transonic Speeds by the NACA Wing-Flow Method
- Investigation of Drag and Pressure Recovery of a Scoop Inlet in the Transonic Speed Range
- Investigation of an NACA 4-(5)(05)-041 Four-Blade Propeller With Several Spinners at Mach Numbers Up to 0.90
- Flight Investigation From Mach Number 0.8 to 2.0 to Determine Some Effects of Wing-to-Tail Distance on the Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Canard Missile
- Flight Measurements at Mach Numbers From 1.1 to 1.9 of the Zero-Lift Drag of a Twin-Engine Supersonic Ram-Jet Configuration
- Handling Qualities of High-Speed Airplanes
- Hydrodynamic Directional Behavior of a Swept Planing-Tail Hull
- An Investigation of the Stream-Tube Power Losses and an Improvement of the Diffuser-Entrance Nose in the Langley 8-Foot Transonic Tunnel
- Investigation of Turbines for Driving Supersonic Compressors 2: Performance of First Configuration With 2.2 Percent Reduction in Nozzle Flow Area