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- Measurement of Static Pressure on Aircraft
- Measurement of Static Forces on Internally Carried Bombs of Three Fineness Ratios in Flow Field of a Swept-Wing Fighter-Bomber Configuration at a Mach Number of 1.61 With Illustrative Drop-Path Calculations
- A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient
- A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient
- A Flight Investigation to Determine the Effectiveness of Mach Number 1.0, 1.2, and 1.41 Fuselage Indentations for Reducing the Pressure Drag of a 45 Degree Sweptback Wing Configuration at Transonic and Low Supersonic Speeds
- Flight Investigation of Factors Affecting the Choice of Minimum Approach Speed for Carrier-Type Landings of a Swept-Wing Jet Fighter Airplane
- Flight Investigation of a Supersonic Propeller on a Propeller Research Vehicle at Mach Numbers to 1.01
- High-Pressure Blowing Over Flap and Wing Leading Edge of a Thin Large-Scale 49 Degree Swept Wing-Body-Tail Configuration in Combination With a Drooped Nose and a Nose With a Radius Increase
- Low-Speed Cascade Investigation of Thin Low-Camber Naca 65-Series Blade Sections at High Inlet Angles
- Measurement of Aerodynamic Heat Transfer to a Deflected Trailing-Edge Flap on a Delta Fin in Free Flight at Mach Numbers From 1.5 to 2.6
- Lateral Stability Investigation at Mach Numbers From 0.8 to 1.7 of Two Rocket-Boosted Models of an Airplane Configuration With a 45 Degree Swept Wing and a Low Horizontal Tail
- Investigation of the Low-Speed Performance and Static Longitudinal Stability and Control Characteristics of a 60 Degree Delta-Wing-Body-Tail Combination With Blowing Over Trailing-Edge Flaps
- Investigation of the Low-Speed Stability and Control Characteristics of a 1/7-Scale Model of the North American X-15 Airplane
- Preliminary investigation of the altitude performance of pentaborane and a pentaborane : JP-4 blend in an experimental 9.5-inch-diameter tubular combustor
- Ground Effects on the Longitudinal Characteristics of Two Models With Wings Having Low Aspect Ratio and Pointed Tips
- Flutter Characteristics at Transonic Speeds of a 45 Degree Sweptback Wing With and Without Inboard Modifications at the Leading and Trailing Edges
- Flutter and Divergence of Rectangular Wings of Very Low Aspect Ratio
- Free-Flight Aerodynamic-Heating Data to a Mach Number of 15.5 on a Blunted Conical Nose With a Total Angle of 29 Degrees
- Heat Transfer Measured on a Flat-Face Cylinder in Free Flight at Mach Numbers Up to 13.9
- Horizontal-Tail Parameters as Determined From Flight-Test Tail Loads on a Flexible Swept-Wing Jet Bomber
- A General System for Calculating Burning Rates of Particles and Drops and Comparison of Calculated Rates for Carbon, Boron, Magnesium, and Isooctane
- Heat Transfer and Boundary-Layer Transition on a Highly Polished Hemisphere-Cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 10(Exp 6)
- Heat-Transfer and Pressure Distribution on Six Blunt Noses at a Mach Number of 2
- Heat-Transfer and Pressure Measurements From a Flight Test of a 1/18-Scale Model of the Titan Intercontinental Ballistic Missile Up to a Mach Number of 3.95 and Reynolds Number Per Foot of 23 X 10(Exp 6): Coord. No. AF-AM-70
- Free-Flight Determination of Boundary-Layer Transition and Heat Transfer for a Hemisphere-Cylinder at Mach Numbers to 5.6
- Flight Performance of a 2.8 KS 8100 Cajun Solid-Propellant Rocket Motor
- Flutter Investigation on the High Subsonic and Transonic Speed Range on Cantilever Delta-Wing Plan Forms With Leading-Edge Sweepback of 60 Degrees, 53 Degrees 8', and 45 Degrees
- Investigation at Transonic Speeds of the Effects of Inlet-Lip Sweep on the Internal-Flow Characteristics of a Semielliptical Air Inlet With an Inlet-Lip Stagger of 30 Degrees
- Investigation of a 0.6 Hub-Tip Radius-Ratio Transonic Turbine Designed for Secondary-Flow Study 1: Design and Experimental Performance of Standard Turbine
- Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area: Detailed Blade-Element Performance
- Calculated Effect of Some Airplane Handling Techniques on the Ground-Run Distance in Landing on Slippery Runways
- A Low-Speed Investigation of the Magnus Effects on a Sting-Mounted Model of a Typical Mortar Shell
- Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 1295
- Aerodynamic interference of slender wing-tail combinations
- Aerodynamic Characteristics of a Circular Cylinder at Mach Number 6.86 and Angles of Attack Up to 90 Degrees
- Abnormal grain growth in nickel-base heat-resistant alloys
- Abnormal grain growth in M-252 and S-816 alloys
- Experimental lift of low-aspect-ratio triangular wings at large angles of attack and supersonic speeds
- Performance of multiple jet-exit installations
- Ground reflection of jet noise
- Performance of basic XJ79-GE-1 turbojet engine and its components
- Simulator studies of jet reaction controls for use at high altitude
- Preliminary studies of rolling-contact fatigue life of high-temperature bearing materials
- Correlation of turbulent heat transfer in a tube for the dissociating system N204 reversibly yields 2N02
- Investigation at supersonic speeds of the compressor stall and inlet buzz characteristics of a J34 - spike-inlet combination
- Comparison of experimentally and analytically determined windmilling characteristics of a compressor with low over-all pressure ratio
- Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40©� sweepback
- Some measurements at subsonic speeds of the aerodynamic forces and moments on two delta wings of aspect ratios 2 and 4 oscillating about the midchord
- Investigation of fixed-geometry supersonic inlets with bypass ducts for matching turbojet-engine air-flow requirements over a range of transonic and supersonic speeds
- Effect at high subsonic speeds of fuselage forebody strakes on the static stability and vertical-tail-load characteristics of a complete model having a delta wing