Free-spinning Wind-tunnel Tests of a Low-wing Monoplane with Systematic Changes in Wings and Tails III : Mass Distributed Along the Wings
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Seidman, Oscar↗
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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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Theoretical calculation of the pressure distribution, span loading, and rolling moment due to sideslip at supersonic speeds for thin sweptback tapered wings with supersonic trailing edges and wing tips parallel to the axis of wing symmetry
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Margolis, Kenneth↗
Experimental Steady-state Yawing Derivatives of a 60 Degree Delta-wing Model as Affected by Changes in Vertical Position of the Wing and in Ratio of Fuselage Diameter to Wing Span
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Jaquet, Byron M↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Subsonic Mach and Reynolds Number Effects on the Characteristics of the Wing and on the Effectiveness of an Elevon
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Reynolds, Robert M↗
The High-speed Aerodynamic Effects of Modifications to the Wing and Wing-fuselage Intersection of an Airplane Model with the Wing Swept Back 35 Degrees
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Boddy, Lee E↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Investigation at a Mach Number of 1.53 to Determine the Effects of Cambering and Twisting the Wing for Uniform Load at a Lift Coefficient of 0.25
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Madden, Robert T↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics Throughout the Subsonic Speed Range with the Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
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Jones, J Lloyd↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics for Symmetrical Wing Sections at High Subsonic and Moderate Supersonic Mach Numbers
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Mas, Newton A↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effects at Subsonic Speeds of a Constant-chord Elevon on a Wing Cambered and Twisted for a Uniform Load at a Lift Coefficient of 0.25
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Jones, J Lloyd↗
Experimental Investigation of Various Wing-mounted External Stores on a Wing-fuselage Combination Having a Sweptback Wing of Inverse Taper Ratio
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Spreemann, Kenneth P↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics at Supersonic Speeds of a Model with the Wing Twisted and Cambered for Uniform Load
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Hall, Charles F↗
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
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Hall, Albert W↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effect of Sideslip on Aerodynamic Characteristics at a Mach Number of 1.4 with the Wing Twisted and Cambered
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Lessing, Henry C↗
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↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effect of Reynolds Number at Supersonic Mach Numbers on the Longitudinal Characteristics of a Wing Twisted and Cambered for Uniform Load
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Heitmeyer, John C↗
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↗
Wing-on and Wing-off Longitudinal Characteristics of an Airplane Configuration Having an Thin Unswept Tapered Wing of Aspect Ratio 3, as Obtained from Rocket-propelled Models at Mach Numbers from 0.8 to 1.4
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Gillis, Clarence L↗
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↗