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NACA Research Memorandums
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NACA Research Memorandums
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1950-1959
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Effects of Wing Flaps and Wing Duct Inlet on the Lift and Stalling Characteristics of a 1/4-Scale Partial-Span Model of the Republic XF-12 Airplane in the Langley 19-Foot Pressure Tunnel
Low-speed pressure-distribution and flow investigation for a large pitch and yaw range of three low-aspect-ratio pointed wings having leading edge swept back 60 degrees and biconvex sections
Performance of Axial-Flow Supersonic Compressor of the XJ55-FF-1 Turbojet Engine. 4 - Analysis of Compressor Operation over a Range of Equivalent Tip Speeds from 801 to 1614 Feet Per Second
Aerodynamic characteristics extended to high angles of attack at transonic speeds of a small-scale 0 degree sweep wing, 45 degree sweptback wing, and 60 degree delta wing
Drag Measurements at Low Lift of a Four-Nacelle Airplane Configuration Having a Longitudinal Distribution of Cross-Sectional Area Conducive to Low Transonic Drag Rise
Drag Measurements at Low Lift of a Four-Nacelle Airplane Configuration Having a Longitudinal Distribution of Cross-Sectional Area Conductive to Low Transonic Drag Rise
Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the Convair YF-102 Airplane in the Langley Free-Flight Tunnel
Pressure Drag of Bodies at Mach Numbers Up to 2.0
Analysis and Construction of Design Charts for Turbines with Downstream Stators
Application of non-afterburning turbojets to supersonic flight
Effect of inlet flow distortion on compressor stall and acceleration characteristics of a J65-B-3 turbojet engine
Effect of leading-edge sweepback on lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 and taper ratio 0.4 at subsonic and supersonic speeds
Experimental investigation of a surge control on a turbojet engine
An Investigation of the Effects of Nose and Lip Shapes for an Underslung Scoop Inlet at Mach Numbers from 0 to 1.9
Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70
A study of conical camber for triangular and sweptback wings
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