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NACA Research Memorandums
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NACA Research Memorandums
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1950-1959
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Wind-Tunnel Data on the Longitudinal and Lateral-Directional Rotary Derivatives of a Straight-Wing, Research Airplane Configuration at Mach Numbers From 2.5 to 3.5
Analysis of V-G records from ten types of Navy airplanes in squadron operations during the period 1949 to 1953
Development of a new flutter testing technique using a towed dynamic airplane model equipped with an automatic stabilizing system: Experimental and calculated dynamic stability characteristics for speeds up to 200 mph
Effects of Free-Flight Rocket-Model Booster-Adapter Configurations on the Aerodynamic Characteristics in Pitch and Sideslip of a Swept-Wing Fighter Airplane Model at a Mach Number of 2.01
Effects of free-flight rocket-model booster-adapter configurations on the aerodynamic characteristics in pitch and sideslip of a swept-wing fighter airplane model at a Mach number of 2.01
Flight-determined pressure distributions over a section of the 35 degree swept wing of the Douglas D-558-II research airplane at Mach numbers up to 2.0
Preliminary Results of an Investigation at Transonic Speeds to Determine the Effects of a Heated Propulsive Jet on the Drag Characteristics of a Related Series of Afterbodies
The Effect of Nacelle Location on the Zero-Lift Drags of 45 Degree Sweptback Wing-Body Configurations Having Boattail and Cylindrical Afterbodies as Determined by Flight Tests at Transonic Speeds
Effects of base bleed on the base pressure of blunt-trailing-edge airfoils at supersonic speeds
Flight Test of an End-Burning Solid-Fuel Ramjet
Transonic Wind-Tunnel Investigation of the Effects of Body Indentation on the Aerodynamics of a Semielliptical Sweptback Wing-Root Inlet Configuration
Investigation of Spoilers at a Mach Number of 1.93 to Determine the Effects of Height and Chordwise Location on the Section Aerodynamic Characteristics of a Two-Dimensional Wing
Free-flight investigation of longitudinal stability and control of a rocket-propelled missile model having cruciform, triangular, inline wings and tails
Flight Investigation of 6.25-Inch-Diameter Deacon Rocket and 10-Inch-Scale Model Rocket
An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data
Performance of supersonic axial-flow compressors based on one-dimensional analysis
A preliminary experimental investigation of a submerged cascade inlet
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