Aerodynamic Characteristics of Several Hypersonic Boost-glide-type Configurations at Mach Numbers from 2.30 to 4.63
Aerodynamic Characteristics of Several Hypersonic Boost-glide-type Configurations at Mach Numbers from 2.30 to 4.63

Author: Ernald B. Graves

Publisher:

Published: 1968

Total Pages: 29

ISBN-13:

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An investigation has been conducted at Mach numbers from 2.30 to 4.63 to determine the static aerodynamic characteristics of several configurations designed for flight at hypersonic Mach numbers. Two all-wing and three wing-body configurations were tested through an angle-of-attack range from about -4° to 33° and an angle-of-sideslip range from about -4° to 8° at a Reynolds number of 3 x 106 per foot (9.84 x 106 meter). The results of the investigation indicated that the wing-body configurations produced higher values of maximum lift-drag ratio than those produced by the all-wing models. The high-body configurations tend to have a self-trimming capability as opposed to that for the low wing-body configurations. Each of the configurations produced a positive dihedral effect that increased with increasing angle of attack and decreased with increasing Mach number. The high wing-body models produced decreasing values of directional stability with increase in angle of attack, whereas the low wing-body models provided increasing values of directional stability with increase in angle of attack.

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

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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.

Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 9.45
Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 9.45

Author: John R. Krouse

Publisher:

Published: 1966

Total Pages: 78

ISBN-13:

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Wind-tunnel tests were conducted at a Mach number of 9.45 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to-drag ratios of all high-wing configurations varied slightly over an angle-of-attack range of 0 degrees to 12 degrees, reaching a maximum value of 2.7 around 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.0 near 12 degrees. In all cases, fuselage base drag accounted for less than 4 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were unstable, unbalanced, or both; whereas several high-wing configurations were both stable and balanced. (Author).

Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 6.26
Longitudinal Aerodynamic Characteristics of Several Hypersonic Aircraft Configurations at a Mach Number of 6.26

Author: John R. Krouse

Publisher:

Published: 1966

Total Pages: 42

ISBN-13:

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Wind-tunnel tests were conducted at a Mach number of 6.26 to determine the longitudinal aerodynamic characteristics of several conceptual hypersonic aircraft configurations, consisting of various half-cone-cylinder bodies and double-delta wings. Effects of body volume, vehicle orientation, wing planform, and wing-tip dihedral were determined. In general, the lift-to-drag ratios of all high-wing configurations varied slightly over an angle-of-attack range of 0 degrees to 12 degrees reaching maximum values of roughly 3.2 near 6 degrees. On the other hand, the lift-to-drag ratios of all low-wing configurations increased continuously with increasing angle of attack, eventually reaching maximum values of roughly 3.6 near 10 degrees. In all cases, fuselage base drag accounted for less than 10 percent of the total drag. For the arbitrarily chosen center-of-gravity location, all low-wing configurations were stable but unbalanced; whereas several high-wing configurations were both stable and balanced. (Author).