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Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6

Author: Walter P. Nelms

Publisher:

Published: 1971

Total Pages: 108

ISBN-13:

Aerodynamic characteristics of a model designed to represent an all body, hypersonic cruise aircraft are presented for Mach numbers from 0.65 to 10.6. The configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section. Detailed effects of varying angle of attack (-2 to 15 deg), angle of sideslip (-2 to 8 deg), Mach number, and configuration buildup were considered. In addition, the effectiveness of horizontal tail, vertical tail, and canard stabilizing and control surfaces was investigated. The results indicate that all configurations were longitudinally stable near maximum lift drag ratio. The configurations with vertical tails were directionally stable at all angles of attack. Trim penalties were small at hypersonic speeds for a center of gravity location representative of the airplane, but because of the large rearward travel of the aerodynamic center, trim penalties were severe at transonic Mach numbers.

Effects of Body Shape on the Aerodynamic Characteristics of an All-body Hypersonic Aircraft Configuration at Mach Numbers from 0.65 to 10.6

Author: Walter P. Nelms

Publisher:

Published: 1972

Total Pages: 68

ISBN-13:

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Aerodynamic Characteristics of a Hypersonic Transport Configuration at Mach 6.86

Author: William John Small

Publisher:

Published: 1970

Total Pages: 36

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Hypersonic Aerodynamic Characteristics of an All-body Research Aircraft Configuration

Author: Louis E. Clark

Publisher:

Published: 1973

Total Pages: 52

ISBN-13:

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An experimental investigation was conducted at Mach 6 to determine the hypersonic aerodynamic characteristics of an all-body, delta-planform, hypersonic research aircraft (HYFAC configuration). The aerodynamic characteristics were obtained at Reynolds numbers based on model length of 2.84 million and 10.5 million and over an angle-of-attack range from minus 4 deg to 20 deg. The experimental results show that the HYFAC configuration is longitudinally stable and can be trimmed over the range of test conditions. The configuration had a small degree of directional stability over the angle-of-attack range and positive effective dihedral at angles of attack greater than 2 deg. Addition of canards caused a decrease in longitudinal stability and an increase in directional stability. Oil-flow studies revealed extensive areas of separated and vortex flow on the fuselage lee surface. A limited comparison of wind-tunnel data with several hypersonic approximations indicated that, except for the directional stability, the tangent-cone method gave adequate agreement at control settings between 5 deg and minus 5 deg and positive lift coefficient. A limited comparison indicated that the HYFAC configuration had greater longitudinal stability than an elliptical-cross-section configuration, but a lower maximum lift-drag ratio.