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NACA Research Memorandums
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Effects of angle of attack and airfoil profile on the two-dimensional flutter derivatives for airfoils oscillating in pitch at high subsonic speeds
Analytical Study of the Effect of Center-of-Gravity Position on the Response to Longitudinal Control in Landing Approaches of a Swept-Wing Airplane of Low Aspect Ratio Having No Horizontal Tail
Investigation of Ejection Release Characteristics of Four Dynamically Scaled Internal-Store Shapes From a 1/17-Scale Simulated Bomb Bay of the Republic F-105 Airplane at Mach Numbers of 1.39 and 1.98
Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
Preliminary investigation of molybdenum disulfide-air-mist lubrication for roller bearings operating to DN values of 1 x 10(exp 6) and ball bearings operating to temperatures of 1000 degrees F
Flight Determination of Drag and Pressure Recovery of a Nose Inlet of Parabolic Profile at Mach Numbers From 0.8 to 1.7
A theory for stability and buzz pulsation amplitude in ram jets and an experimental investigation including scale effects
Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range
Investigation of Adjustable Supersonic Inlet in Combination With J34 Engine Up to Mach 2.0
Observation of Laminar Flow on a Blunted 15 Degree Cone-Cylinder in Free Flight at High Reynolds Numbers and Free-Stream Mach Numbers to 8.17
Analytical investigation of single-stage-turbine efficiency characteristics in terms of work and speed requirements
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)
Flight Characteristics of a 1/4-Scale Model of the XFV-1 Airplane (TED No. NACA DE-378)
Experimental Pressure Distribution on Fuselage Nose and Pilot Canopy of Supersonic Airplane at Mach Number 1.90
Measurements of Aerodynamic Heat Transfer and Boundary-Layer Transition on a 15 Degree Cone in Free Flight at Supersonic Mach Numbers Up to 5.2
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