Lanterna Rally
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Wind-tunnel Investigation of Aerodynamic Efficiency of Three Planar Elliptical Wings with Curvature of Quarter-chord Line
Transonic Wind-tunnel Investigation of Aerodynamic-loading Characteristics of a 2-percent-thick Trapezoidal Wing in Combination with Basic and Indented Bodies
Author: Thomas C. Kelly
Publisher:
Published: 1957
Total Pages: 82
ISBN-13:
DOWNLOAD EBOOK →Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Measurements of Section Characteristics of a 45 Degree Swept Wing Spanning a Rectangular Low-speed Wind Tunnel as Affected by the Tunnel Walls
Author: Robert E. Dannenberg
Publisher:
Published: 1950
Total Pages: 678
ISBN-13:
DOWNLOAD EBOOK →Tunnel-wall corrections for the induced upwash velocity for a swept wing completely spanning a rectangular wind tunnel are included in the appendix.
A Wind Tunnel Investigation of the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2.37, 2.98, and 3.90
Wind Tunnel Investigation of Three Axisymmetric Cowls of Different Lengths at Mach Numbers from 0.60 to 0.92
Low-speed Wind Tunnel Investigation of the Aerodynamic Characteristics of an Airplane Having a Cambered Arrow Wing with a 75 Deg Swept Leading Edge
Wind-tunnel Investigation of an Advanced General Aviation Canard Configuration
Wind Tunnel Measurements of Hysteresis in the Static Aerodynamic Characteristics of Aircraft
Wind-tunnel Investigation of the Aerodynamic Characteristics in Pitch of Wing-fuselage Combinations at High Subsonic Speeds
Author: Thomas J. King
Publisher:
Published: 1956
Total Pages: 36
ISBN-13:
DOWNLOAD EBOOK →The results presented in the present paper represent a continuation of a research program conducted in the Langley high-speed 7- by 10-foot tunnel to investigate the aerodynamic characteristics in pitch, sideslip, and steady roll of model configurations having variations in the wing geometric parameters. Presented herein are the aerodynamic characteristics in pitch of wing-fuselage combinations with wings having an aspect ratio of 4, a sweepback angle of 45 degrees, end taper ratios of 0.3, 0.6,and 1.0. The Mach number range was from 0.40 to about 0.95 and the Reynolds number range was from 2,000,000 to 3,000,000.
