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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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NACA Research Memorandums
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NACA Research Memorandums
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National Advisory Committee for Aeronautics Collection
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Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Investigation of the Effect of Balancing Tabs on the Hinge-Moment Characteristics of a Trailing-Edge Flap-Type Control on a Trapezoidal Wing at a Mach Number of 1.61
Comparison Between Theoretical and Experimental Rates of Roll of Two Models with Flexible Rectangular Wings at Supersonic Speeds
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance
Measurements of Aerodynamic Characteristics of a 35 Degree Sweptback NACA 65-009 Airfoil Model With 1/4-Chord Plain Flap by the NACA Wing-Flow Method
Calculative method for estimating the interference pressure field at zero lift on a symmetrical swept-back wing mounted on a circular cylindrical body
Effects of simulated skin wrinkles on the wing surface on the aerodynamic characteristics of two wing-body combinations employing wings of low aspect ratio at subsonic and supersonic speeds
Aerodynamic characteristics of several tip controls on a 60 degree wing at a Mach number of 1.61
A Compilation of Summaries From NACA Reports on Fuels Research, 1945-1952
Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6)
Magnesium-slurry combustion performance in 6.5-inch-diameter ram-jet engine mounted in connected-pipe facility
Relation of Turbojet and Ramjet Combustion Efficiency to Second-Order Reaction Kinetics and Fundamental Flame Speed
Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor
Boron and zirconium from crucible refractories in a complex heat-resistant alloy
Stall and flame-out resulting from firing of armament
Langley Full-Scale-Tunnel Investigation of Maximum Lift and Stability Characteristics of an Airplane Having Approximately Triangular Plan Form (DM-1 Glider)
Investigation of Sea-Level Performance of I-16 Turbojet Engine at Zero Ram with XFR-1 Intake Duct Shroud, and Tail Pipe
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 4 - Analysis of Compressor Performance
Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine, 3, Performance Characteristics with the High-Flow Compressor
Summary of Information Relating to Gust Loads on Airplanes
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