Effects of body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration at Mach numbers from 0.65 to 10.6
01 May 1972-
TL;DR: In this article, an experimental investigation was conducted to determine the effects of several variations in body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration, including the ratio of maximum cross-sectional to body planform area, body leading-edge sweep, and forebody length ratio.
Abstract: An experimental investigation was conducted to determine the effects of several variations in body shape on the aerodynamic characteristics of an all-body hypersonic aircraft configuration. The basic configuration had a delta planform with an elliptic cone forebody and an afterbody of elliptic cross section terminating in a straight-line trailing edge. Variations in body shape included the ratio of maximum cross-sectional to body planform area, body leading-edge sweep, and forebody length ratio. In addition, the effects of a thin wing mounted on one of the bodies was investigated, and the aerodynamic characteristics of just the forebodies of two of the configurations were determined. The models had no stabilizing surfaces or propulsion system packages. Ranges of angle of attack (-4 deg to +15 deg) and angle of sideslip (-4 deg to +8 deg) were investigated. Of the four complete bodies, the configuration with the lowest ratio of cross-sectional to body planform area had the highest maximum lift-drag ratio and the greatest level of longitudinal stability at most Mach numbers. All the configurations had positive longitudinal stability near maximum lift-drag ratio at most Mach numbers. With exception of the lowest subsonic Mach numbers, changes in body sweep angle and in forebody length ratio had only minor effects on maximum lift-drag ratio.
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01 Dec 1978
TL;DR: In this paper, the aerodynamic influence coefficients calculated using an existing linear theory program were used to modify the pressures calculated using impact theory, and the combined approach gave improved predictions of the local pressure and loadings over either linear theory alone or impact theory alone.
Abstract: The aerodynamic influence coefficients calculated using an existing linear theory program were used to modify the pressures calculated using impact theory. Application of the combined approach to several wing-alone configurations shows that the combined approach gives improved predictions of the local pressure and loadings over either linear theory alone or impact theory alone. The approach not only removes most of the short-comings of the individual methods, as applied in the Mach 4 to 8 range, but also provides the basis for an inverse design procedure applicable to high speed configurations.
6 citations
01 Jun 1969
TL;DR: Experimental and theoretical study of symmetrical and cambered delta wing configuration between Mach 2.0 and 10.7 was carried out in this paper, where the authors proposed a model of the delta wing.
Abstract: Experimental and theoretical study of symmetrical and cambered delta wing configuration between Mach 2.0 and 10.7
1 citations
01 Oct 1970
TL;DR: Longitudinal aerodynamic stability of three hypersonic aircraft at Mach numbers from 0065 to 1070 was analyzed in this paper, showing that the aircraft were able to maintain the same speed at all Mach numbers.
Abstract: Longitudinal aerodynamic stability of three hypersonic aircraft at Mach numbers from 0065 to 1070
1 citations
01 Jan 1973
TL;DR: In this article, a limited comparison of wind-tunnel data wlth several hypersonic approximations indicated that except for the directional stability, the tangent-cone method gave adequate agreement at control settings between 50 and -50 and positive lift coefficient.
Abstract: at angles of attack greater than 2'. Addition of canards caused a decrease in long- tudinal stability and an ir~crease in directional stabilitv. Oil-flow studies revealed exten- sive areas of separated and vortex flow on the fuselage lee surface. A limited comparison of wind-tunnel data wlth several hypersonic approximations indicated that. except for the directional stability, the tangent-cone method gave adequate agreement at control settings between 50 and -50 and positive lift coefficient.
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01 Nov 1971
TL;DR: In this paper, the 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.
Abstract: 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.
7 citations