The design of variable Mach number asymmetric supersonic nozzles by two procedures employing inclined and curved sonic lines
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NOZZLES↗
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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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The Aerodynamic Characteristics of an Aspect-ratio-20 Wing Having Thick Airfoil Sections and Employing Boundary-layer Control by Suction
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Cocke, Bennie W , Jr↗
An investigation of a wing-propeller configuration employing large-chord plain flaps and large-diameter propellers for low-speed flight and vertical take-off
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Kuhn, Richard E↗
General theory of wave-drag reduction for combinations employing quasi-cylindrical bodies with an application to swept-wing and body combinations
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Nielsen, Jack N↗
An Evaluation of the Effects of Flexibility on Wing Strains in Rough Air for a Large Swept-wing Airplane by Means of Experimentally Determined Frequency-response Functions with an Assessment of Random-process Techniques Employed
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Coleman, Thomas L↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Investigation of a Large-scale Model at Low Speed
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Mccormack, Gerald 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↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Characteristics at a Mach Number of 1.53 Including Effect of Small Variations of Sweep
Measured values of lift, drag, and pitching moment at a Mach number of 1.53 and Reynolds numbers of 0.31, 0.62, and 0.84 million are presented for a wing-fuselage combination having a wing leading-edge sweep angle of 63 degrees, an aspect ratio of 3.42, a taper ratio of 0.25, and an NACA 64A006 section in the stream direction. Data are also presented for sweep angles of 57.0 degrees, 60.4 degrees, 67.0 degrees, and 69.9 degrees. The experimentally determined characteristics were less favorable than indicated by the linear theory but the experimental and theoretical trends with sweep were in good agreement. Boundary-layer-flow tests showed that laminar boundary-layer separation was the primary cause of the differences between experiment and theory.
REYNOLDS NUMBER EFFECTS - COMPLETE WING↗
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 : Effects of Split Flaps, Elevons, and Leading-edge Devices at Low Speed
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Hopkins, Edward J↗
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 at Supersonic Speeds of Side Scoops Employing Boundary-layer Suction
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Edwards, Sherman S↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Aerodynamic Characteristics in Sideslip of a Large-scale Model Having a 63 Degree Swept-back Vertical Tail
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Mccormack, Gerald M↗
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 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↗
Aerodynamic Study of a Wing-fuselage Combination Employing a Wing Swept Back 63 Degrees : Effectiveness of an Elevon as a Longitudinal Control and the Effects of Camber and Twist on the Maximum Lift-drag Ratio at Supersonic Speeds
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Olson, Robert N↗