Aerodynamic Characteristics at Mach Numbers from 1.50 to 4.63 of a Variable-geometry Lifting Reentry Concept Employing Elevator and Body Base Flaps for Control PDF Download
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Author: Roger H. Fournier
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 76
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Book Description
An investigation of a lifting body configuration has been conducted in the Langley Unitary Plan wind tunnel through a Mach number range from 1.50 to 4.63 to determine the control effectiveness characteristics of body base flaps with and without anhedral tail elevator controls.
Author: Roger H. Fournier
Publisher:
ISBN:
Category : Space vehicles
Languages : en
Pages : 76
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Book Description
An investigation of a lifting body configuration has been conducted in the Langley Unitary Plan wind tunnel through a Mach number range from 1.50 to 4.63 to determine the control effectiveness characteristics of body base flaps with and without anhedral tail elevator controls.
Author: Bernard Spencer
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 80
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 34
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Book Description
Author: Bernard Spencer
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Author: Edward J. Ray
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 112
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Book Description
Author: A. Warner Robins
Publisher:
ISBN:
Category : Hypersonic planes
Languages : en
Pages : 68
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 68
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Book Description
Author: William I. Scallion
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 62
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Book Description
A 0.0196-scale model of the HL-20 lifting body, one of several configurations proposed for future crewed spacecraft, was tested in the Langley 31-Inch Mach 10 Tunnel. The purpose of the tests was to determine the effectiveness of fin-mounted elevons, a lower surface flush-mounted body flap, and a flush-mounted yaw controller at hypersonic speeds. The nominal angle-of-attack range, representative of hypersonic entry, was 20 to 41 degrees, the sideslip angles were 0, 2, and -2 degrees, and the test Reynolds number was 1.06 x 10[factor 6] based on model reference length. The aerodynamic, longitudinal, and lateral control effectiveness along with surface oil flow visualizations are presented and discussed. The configuration was longitudinally and laterally stable at the nominal center of gravity. The primary longitudinal control, the fin-mounted elevons, could not trim the model to the desired entry angle of attack of 30 degrees. The lower surface body flaps were effective for roll control and the associated adverse yawing moment was eliminated by skewing the body flap hinge lines. A yaw controller, flush-mounted on the lower surface, was also effective, and the associated small rolling moment was favorable.
