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National Advisory Committee for Aeronautics Collection
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NACA Research Memorandums
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A radar method of calibrating airspeed installations on airplanes in maneuvers at high altitudes and at transonic and supersonic speeds
Method for Estimating Lift Interference of Wing-Body Combinations at Supersonic Speeds
Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6
An Investigation at Transonic Speeds of the Effects of Fences, Drooped Nose, and Vortex Generators on the Aerodynamic Characteristics of a Wing-Fuselage Combination Having a 6-Percent-Thick, 45 Degree Sweptback Wing
Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile
An Investigation of the Longitudinal Stability and Afterbody Pressure Characteristics of Specialized Store Configurations at Transonic Speeds
Effect of Nose Shape and Wing Thickness Ratio on the Drag at Zero Lift of a Missile Having Triangular Wings and Tails
High-Speed Aerodynamic Characteristics of Four Thin NACA 63-Series Airfoils
Supersonic-Tunnel Tests of Two Supersonic Airplane Model Configurations
Experimental investigation of the effectiveness of various suction-slot arrangements as a means for increasing the maximum lift of the NACA 65(sub 3)-018 airfoil section
Summary of Results of Tumbling Investigations Made in the Langley 20-Foot Free-Spinning Tunnel on 14 Dynamic Models
Effect of wing sweep, taper, and thickness ratio on the transonic drag characteristics of wing-body combinations
Flight Investigation at High-Subsonic, Transonic, and Supersonic Speeds to Determine Zero-Lift Drag of Bodies of Revolution Having Fineness Ratio of 6.04 and Varying Positions of Maximum Diameter
Application of blade cooling to gas turbines
Two-dimensional aerodynamic characteristics of 34 miscellaneous airfoil sections
Vibration Survey of Blades in 10-Stage Axial-Flow Compressor 1: Static Investigation
Experimental Investigation of the Effects of Sweepback on the Flutter of a Uniform Cantilever Wing With a Variably Located Concentrated Mass
The effects of various parameters including Mach number on propeller blade flutter with emphasis on stall flutter
Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04
Free-jet performance of 16-inch ram-jet engine with several fuels
Method for estimating lift interference of wing-body combinations at supersonic speeds
Preliminary evaluation of the air and fuel specific-impulse characteristics of several potential ram-jet fuels 4: hydrogen, a-methylnaphthalene, and carbon
Investigation of a 1/5-scale model of a proposed high-submerged-speed submarine in the Langley full-scale tunnel
A method of analysis of V-G records from transport operations
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