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National Advisory Committee for Aeronautics Collection
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National Advisory Committee for Aeronautics Collection
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Technical Report Archive and Image Library
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NACA Research Memorandums
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NACA Technical Reports
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NACA Research Memorandums
20
NACA Technical Reports
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1951
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1951
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National Advisory Committee for Aeronautics Collection
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1951
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Calculated Performance of a Mercury-Compressor-Jet Powered Airplane Using a Nuclear Reactor as an Energy Source
Measurement of distortion in second experimental control rod for argonne naval reactor with constant transverse temperature gradient and uniform longitudinal temperature distribution
Wing-Flow Study of Pressure-Drag Reduction at Transonic Speed by Projecting a Jet of Air From the Nose of a Prolate Spheroid of Fineness Ratio 6
Free-Spinning Tunnel Investigation of a 1/20-Scale Model of the Douglas X-3 Airplane
Stability and Control Measurements Obtained during USAF-NACA Cooperative Flight-Test Program on the X-4 Airplane (USAF No. 46-677)
Free-flight performance of 16-inch diameter supersonic ram-jet units 4: performance of ram-jet units designed for combustion chamber inlet Mach number of 0.21 at free-stream Mach number of 1.6 over a range flight conditions
Effect of a deflectable wing-tip control on the low-speed lateral and longitudinal characteristics of a large-scale wing with the leading edge swept back 47.5 degrees
Low-Speed Characteristics of a Wing Having 63 Degrees Sweepback and Uniform Camber
Measurement of distortion in second experimental control rod with temperature patterns simulating shim rod out and shim rod 50 percent inserted for Argonne Naval Reactor
Some Effects of Blade Trailing-Edge Thickness on Performance of a Single-Stage Axial-Flow Compressor
Wind-Tunnel Investigation at Mach Numbers From 0.50 to 1.29 of an Unswept, Tapered Wing of Aspect Ratio 2.67 With Leading- and Trailing-Edge Flaps - Flaps Deflected in Combination
The Origin of Aerodynamic Instability of Supersonic Inlets at Subcritical Conditions
Wind-tunnel investigation at Mach numbers from 0.50 to 1.29 of an unswept, tapered wing of aspect ratio 2.67 with leading- and trailing-edge flaps - leading-edge flaps deflected
Base pressures measured on several parabolic-arc bodies of revolution in free flight at Mach numbers from 0.8 to 1.4 and at large Reynolds numbers
Effect of Surface Finish on Fatigue Properties at Elevated Temperatures 1: Low-Carbon N-155 With Grain Size of A.S.T.M. 1
Investigation of wing-tip ailerons on a 51.3 degrees sweptback wing at transonic speeds by the transonic-bump method
The Effect of Raking the Aileron Tips on the Lateral-Control and Hinge-Moment Characteristics of a 20-Percent-Chord Partial-Span Outboard Aileron on a Wing With Leading-Edge Swept Back 51.3 Degrees
Survey of Available Information on Internal Flow Losses Through Axial Turbomachines
Experimental Investigation of Flow in the Rotating Passages of a 48-Inch Impeller at Low Tip Speeds
Investigation of wear and friction properties under sliding conditions of some materials suitable for cages of rolling-contact bearings
A summary of lateral-stability derivatives calculated for wing plan forms in supersonic flow
Resistance of Various Materials to Attack by Molten Bismuth-Lead Eutectic at Elevated Temperatures
Some effects of frequency on the contribution of a vertical tail to the free aerodynamic damping of a model oscillating in yaw
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