Aerodynamic Characteristics of a Wing with Unswept Quarter-chord Line, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A004 Airfoil Section : Transonic-bump Method
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Myers, Boyd C , II↗
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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Lateral-control investigation of flap-type controls on a wing with quarter-chord line swept back 35 degrees, aspect ratio 4, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method
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Thompson, Robert F↗
Lateral-control investigation of flap-type and spoiler-type controls on a wing with quarter-chord-line sweepback of 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic-bump method
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Hammond, Alexander D↗
Aerodynamic Characteristics of a Wing with Quarter-chord Line Swept Back 45 Degrees, Aspect Ratio 6, Taper Ratio 0.6, and NACA 65A009 Airfoil Section
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Spreemann, Kenneth P↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration with a Wing of 45 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfo
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Osborne, Robert S↗
Wing-flow Measurements of Longitudinal Stability and Control Characteristics of a Supersonic Airplane Configuration Having a 42.8 Degree Sweptback Circular Arc Wing with Aspect Ratio 4.0, Taper Ratio 0.50, and Sweptback Tail Surfaces
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Crane, Harold L↗
Effect of an End Plate on the Aerodynamic Characteristics of a 20.55 Degree Sweptback Wing with an Aspect Ratio of 2.67 and a Taper Ratio of 0.5. : Transonic-Bump Method
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Watson, James M↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 60 Degree Sweepback, Aspect-ratio 4, Taper Ratio 0.6, and NACA 65A006 Airf
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Wood, Raymond B↗
Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Triangular Wing of Aspect Ratio 2 with NACA 0008-63 Section
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Smith, Donald W↗
Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Triangular Wing of Aspect Ratio 2 with NACA 0005-63 Section
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Smith, Donald W↗
Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Triangular Wing of Aspect Ratio 4 with NACA 0005-63 Section
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Heitmeyer, John C↗
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : plane triangular wing of aspect ratio 2 with NACA 0003-63 section
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Heitmeyer, John C↗
Lift, Drag, and Pitching Moment of Low-aspect-ratio Wings at Subsonic and Supersonic Speeds : Plane Tapered Wing of Aspect Ratio 3.1 with 3-percent-thick, Biconvex Section
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Reese, David E↗
A Transonic-wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2. : Wing-fuselage Configuration Having a Wing of 0 Degrees Sweepback, Aspect Ratio 4.0,taper Ratio 0.6, and NACA 65A006 Ai
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Cahn, Maurice S↗
A Transonic Wing Investigation in the Langley 8-foot High-speed Tunnel at High Subsonic Mach Numbers and at a Mach Number of 1.2 : Wing-fuselage Configuration Having a Wing of 35 Degrees Sweepback, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006
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Henry, Beverly Z , Jr↗
Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds : triangular wing of aspect ratio 4 with NACA 0005-63 thickness distribution, cambered and twisted for trapezoidal span load distribution
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Phelps, E Ray↗
Investigation in the Ames 12-foot Pressure Wind Tunnel of a Model Horizontal Tail of Aspect Ratio 3 and Taper Ratio 0.5 Having the Quarter-chord Line Swept Back 45 Degrees
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Kolbe, Carl D↗
Aerodynamic Characteristics of Four Wings of Sweepback Angles 0 Degree, 35 Degrees, 45 Degrees, and 60 Degrees, NACA 65A006 Airfoil Section, Aspect Ratio 4, and Taper Ratio 0.6 in Combination with a Fuselage at High Subsonic Mach Numbers and Mach Num
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Luoma, Arvo A↗