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- Some Notes on the Violent Lateral-Longitudinal Coupling Motions of the Douglas X-3 Airplane in Aileron Rolls
- The Static and Dynamic-Rotary Stability Derivatives at Subsonic Speeds of an Airplane Model With an Unswept Wing and a High Horizontal Tail
- A Transonic Wind-Tunnel Investigation of Store and Horizontal-Tail Loads and Some Effects of Fuselage-Afterbody Modifications on a Swept-Wing Fighter Airplane
- Use of Shadowgraph Technique in the Analysis of the Performance of Two Supersonic Axial-Flow Compressor Rotors Operating Over a Mean Radius Relative Inlet Mach Number Range of 0.85 to 1.7
- Wind-Tunnel Investigation of a Ram-Jet Model Having a Wing and Canard Surfaces of Delta Plan Form With 70 Degrees Swept Leading Edges: Force and Moment Characteristics at Combined Angles of Pitch and Sideslip for Mach Number 2.01
- Wind-Tunnel Investigation at High Subsonic Speeds of Some Effects of Fuselage Cross-Section Shape and Wing Height on the Static Longitudinal and Lateral Stability Characteristics of a Model Having a 45 Degree Swept Wing
- The Variation With Wing Aspect Ratio of Flap Effectiveness on Thin Rectangular Wings at Transonic Speeds
- Wind-Tunnel Investigation at Low Speed of Effects of Sideslip on Static Longitudinal Trim and Static Lateral Stability Characteristics of Three Fighter-Type Airplane Models
- Wind-Tunnel Investigation at Mach Numbers From 0.8 to 1.4 of Static Longitudinal and Lateral-Directional Characteristics of an Unswept-Wing Airplane Model
- Wind-Tunnel Investigation at Transonic Speeds of a Jet Control on a 35 Degree Swept Wing: Transonic-Bump Method
- A Transonic Investigation of Changing Indentation Design Mach Number on the Aerodynamic Characteristics of a 45 Degree Sweptback-Wing-Body Combination Designed for High Performance
- Transonic Investigation of the Effectiveness and Loading Characteristics of a Flap-Type Aileron With and Without Paddle Balances of an Unswept-Wing-Fuselage Model
- Transonic Wind-Tunnel Investigation of Static Longitudinal Force and Moment Characteristics of Two Wing-Body Combinations With Clipped-Tip and Full Delta Wings of Aspect Ratio 1.73
- A Transonic Investigation of the Static Longitudinal-Stability Characteristics of a 45 Degree Sweptback Wing-Fuselage Combination With and Without Horizontal Tail
- Transonic Wind-Tunnel Investigation of the Effects of a Heated Propulsive Jet on the Pressure Distribution Along a Fuselage Overhang
- Experimental and Theoretical Studies of Interference Effects on the Damping in Roll of the Bell X-1A Research Airplane at Supersonic Speeds (Including Canopy Shape Effects)
- A Method of Reducing Heat Transfer to Blunt Bodies by Air Injection
- Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
- The Effects of Compressibility on the Upwash at the Propeller Planes of a Four-Engine Tractor Airplane Configuration Having a Wing With 40 Degrees of Sweepback and an Aspect Ratio of 10
- Zero-Lift Drag of a Series of Bomb Shapes at Mach Numbers From 0.60 to 1.10
- The Origin and Distribution of Supersonic Store Interference From Measurement of Individual Forces on Several Wing-Fuselage-Store Configurations 5: Swept-Wing Heavy-Bomber Configuration With Large Store (Nacelle). Mach Number 2.01
- Acoustics of a Nonhomogeneous Moving Medium
- Investigation of Lateral Control Near the Stall: Analysis for Required Longitudinal Trim Characteristics and Discussion of Design Variables
- Performance of Pentaborane, Pentaborane - JP-4 Fuel Mixtures, and Trimethylborate Azeotrope Fuel in a Full-Scale Turbojet Engine
- Wind-Tunnel Measurements of Wing Buffeting on 1/16-Scale Model of Douglas D-558-II Research Airplane
- A Brief Investigation of the Effect of Waves on the Take-Off Resistance of a Seaplane
- Conversion of Inviscid Normal-Force Coefficients in Helium to Equivalent Coefficients in Air for Simple Shapes at Hypersonic Speeds
- Crash Injury
- Effect of Pressure on the Spontaneous Ignition Temperature of Liquid Fuels
- Effect of Blade-Section Camber on Aerodynamic Characteristics of Full-Scale Supersonic-Type Propellers at Mach Numbers to 1.04
- Elevated-Temperature Fatigue Properties of Two Titanium Alloys
- Effects of a Straightening Operation on Performance of Inconel 550 Buckets
- Effects of Rocket-Armament Exhaust Gas on the Performance of a Supersonic-Inlet J34-Turbojet-Engine Installation at Mach 2.0
- Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine
- Effect of Inlet-Guide-Vane Angle on Performance Characteristics of a 13-Stage Axial-Flow Compressor in a Turbojet Engine
- The Effect of Trailing-Edge Bluntness on the Performance of a Small-Scale Supersonic Propeller at Forward Mach Numbers to 0.92
- Experimental Evaluation of Gaseous Hydrocarbon Fuel in a 16-Inch-Diameter Ram-Jet Engine
- The Effect of External Stiffening Ribs on the Rolling Power of Ailerons on a Swept Wing
- Determination of the Structural Damping Coefficients of Six Full-Scale Helicopter Rotor Blades of Different Materials and Methods of Construction
- Dynamic Model Investigation of Two Tail-Sitter Vertically Rising Airplanes to Determine the Altitude Required to Approach Normal Flight Conditions Under Power Failure in Hovering Flight
- Analysis of a Form of Peak Holding Control
- Combined Effects of Wing Taper and Low Horizontal-Tail Position on Longitudinal Stability of a 45 Degree Sweptback Wing-Body Combination at Transonic Speeds
- Comparison With Theory of Landing Impacts of a Model of a Seaplane Incorporating a Hydro-Ski With and Without a Shock Absorber
- The Design of Brittle-Material Blade Roots Based on Theory and Rupture Tests of Plastic Models
- Boundaries of Supersonic Axisymmetric Free Jets
- Blowing Over the Flaps and Wing Leading Edge of a Thin 49 Degree Swept Wing-Body-Tail Configuration in Combination With Leading-Edge Devices
- A Brief Summary of Experience in Boosting Aerodynamic Research Models
- Wind-Tunnel Investigation of the Interference Effects during Separation of a 1/40-Scale Model Convair B-58 Airplane and Store at Mach Numbers of 1.41, 1.61, and 2.01
- Aerodynamic Design of Axial-Flow Compressors, Volume 2
- Aerodynamic Characteristics of a 0.04956-Scale Model of the Convair F-102B Airplane at Mach Numbers of 1.41, 1.61, and 2.01: Coord No. AF-231