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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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At least 379 records · Page 21

All sources NASA NTRS DOE OSTI

NASA NTRS1953

Pressure Distributions About Finite Wedges in Bounded and Unbounded Subsonic Streams

An analytical investigation of incompressible flow about wedges was made to determine effects of tunnel-wedge ratio and wedge angle on the wedge pressure distributions. The region of applicability of infinite wedge-type velocity distribution was examined for finite wedges. Theoretical and experimental pressure coefficients for various tunnel-wedge ratios, wedge angles, and subsonic Mach numbers were compared.

FLOW, LAMINAR↗

NASA NTRS1953

An analytical investigation of the effect of the rate of increase of turbulent kinetic energy in the stream direction on the development of turbulent boundary layers in adverse pressure gradients

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BOUNDARY LAYER - WING SECTIONS↗

NASA NTRS1954

A flight investigation of the practical problems associated with porous-leading-edge suction

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BOUNDARY-LAYER CONTROL - COMPLETE WINGS↗

NASA NTRS1947

An Investigation of the Lateral-control Characteristics of Spoilers on a High-aspect-ratio Wing of NACA 65-210 Section in the Langley 8-foot High Speed Tunnel

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Luoma, Arvo A↗

NASA NTRS1950

Low-speed aerodynamic characteristics of a series of swept wings having NACA 65A006 airfoil sections

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Cahill, Jones F↗

NASA NTRS1950

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback

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Spearman, M Leroy↗

NASA NTRS1950

Low-speed Aerodynamic Characteristics of a Series of Swept Wings Having NACA 65A006 Airfoil Sections

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Cahill, Jones F↗

NASA NTRS1950

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Static Longitudinal Stability and Control Characteristics at a Mach Number of 1.59

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Spearman, M Leroy↗

NASA NTRS1950

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59

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Spearman, M Leroy↗

NASA NTRS1950

Pressure coefficients at Mach numbers from 0.60 to 0.85 for a semispan wing with NACA 0012-64 section, 20-percent-chord plain aileron, and 0 degree and 45 degree sweepback

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Krumm, Walter J↗

NASA NTRS1950

Preliminary results of the flight investigation between Mach numbers of 0.80 and 1.36 of a rocket-powered model of a supersonic airplane configuration having a tapered wing with circular-arc sections and 40 degree sweepback

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D'Aiutolo, Charles T↗

NASA NTRS1950

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Static Lateral Control Characteristics at Mach Numbers of 1.40 and 1.59

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Robinson, Ross B↗

NASA NTRS1951

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degree Sweepback : Force Characteristics of the Complete Configuration and Its Various Components at Mach Numbers of 1.40 and 1.59

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Smith, Norman F↗

NASA NTRS1951

Comparison of Airfoil Sections on Two Triangular-wing-fuselage Configurations at Transonic Speeds from Tests by the NACA Wing-flow Method

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Hall, Albert W↗

NASA NTRS1952

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback

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Gapcynski, John P↗

NASA NTRS1952

An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing with Circular-arc Sections and 40 Degrees Sweepback : Estimated Downwash Angles Derived from Pressure Measurements on the Tail at Mach Numbers of 1.40 and 1.59

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Grant, Frederick C↗

NASA NTRS1953

Effects of roughness and Reynolds number on the nonlinear lift characteristics of a wing with modified hexagonal airfoil sections

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Schwartzberg, Milton A↗

NASA NTRS1954

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 1.45 and 1.97

Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 1.45 and 1.97. The investigation includes some comparison of the effects of Reynolds number and of thickening the wing root sections on the loading.

Kaattari, George E↗