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NACA Research Memorandums
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NACA Research Memorandums
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1950-1959
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Flight Measurements of the Lateral Response Characteristics of the Convair XF-92A Delta-Wing Airplane
Flight Determination of the Longitudinal Stability and Control Characteristics of a 0.125-Scale Rocket-Boosted Model of the Mcdonnell F-101 Airplane at Mach Numbers from 0.82 to 1.84
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
Wind-Tunnel Tests of the Static Longitudinal Characteristics at Low Speed of a Swept-Wing Airplane With Blowing Flaps and Leading-Edge Slats
Experimental Investigation of the Transonic and Supersonic Flutter Characteristics of the Upper and Lower Vertical Tails of an Air-to-Ground Missile
Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine
Aircraft configurations developing high lift-drag ratios at high supersonic speeds
Icing Characteristics and Anti-Icing Heat Requirements for Hollow and Ternally Modified Gas-Heated Inlet Guide Vanes
Effects of Surface Roughness and Extreme Cooling on Boundary-Layer Transition for 15 Degrees Cone-Cylinder in Free Flight at Mach Numbers to 7.6
Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance
Aerodynamics of Missiles Employing Wings of Very Low Aspect Ratio
Comparison of Free-Flight Measurements of the Zero-Lift Drag Rise of Six Airplane Configurations and Their Equivalent Bodies of Revolution at Transonic Speeds
Full-Scale Investigation of Boundary-Layer Control by Suction Through Leading-Edge Slots on a Wing-Fuselage Configuration Having 47.5 Degree Leading-Edge Sweep With and Without Flaps
Measurement of Uniform Flame Movement in Carbon Monoxide - Air Mixtures Containing Either Added D2O or H2O
Preliminary Investigation of the Transonic Characteristics of an NACA Submerged Inlet
Experimental Investigation of Supersonic Flow With Detached Shock Waves for Mach Numbers Between 1.8 and 2.9
Aerodynamic Characteristics at a Mach Number of 1.25 of a 6-Percent-Thick Triangular Wing and 6- and 9-Percent-Thick Triangular Wings in Combination With a Fuselage: Wing Aspect Ratio 2.31, Biconvex Airfoil Sections
Flight determination of the effects of rudder-pedal-force characteristics on the aiming error in azimuth of a conventional fighter airplane
Free-flight performance of 16-inch-diameter supersonic ram-jet units 2: five units designed for combustion-chamber-inlet Mach number of 0.16 at free-stream Mach number of 1.60 (units B-1, B-2, B-3, B-4, and B-5)
Effect of air distribution on radial temperature distribution in one-sixth sector of annular turbojet combustor
Experimental investigation of air-cooled turbine blades in turbojet engine 9: evaluation of the durability of noncritical rotor blades in engine operation
Comparison of Transonic Characteristics of Lifting Wings From Experiments in a Small Slotted Tunnel and the Langley High-Speed 7- by 10-Foot Tunnel
Investigation of dynamic characteristics of a turbine-propeller engine
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