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Author: Louis S. Stivers
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 26
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Book Description
Author: Louis S. Stivers
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 26
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Book Description
Author: William J. Small
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 66
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Book Description
Author: Walter P. Nelms
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 108
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Book Description
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.
Author:
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 60
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Author: Bernard Spencer
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
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Author: Vernon Van Hise
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 24
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Book Description
A systematic study of induced pressures on a series of bodies of revolution with varying nose bluntness has been made by using the method of characteristics for a perfect gas. The fluid mediums investigated were air and helium and the Mach number range was from 5 to 40. A study of representative shock shapes was also made. Flow parameters obtained from the blast-wave analogy gave good correlations of induced pressures and shock shapes. The induced-pressure correlations yielded empirical equations for air and helium which cover the complete range of nose bluntness considered. (Nose fineness ratios varied from 0.4 to 4.) Available experimental results were in good agreement with the characteristics solutions. Properties connected with the concept of hypersonic similitude enabled correlations of the calculations to be made with respect to nose shape, Mach number, and ratio of specific heats.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 598
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Author: H. Reese Ivey
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 28
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Book Description
A method is developed for calculating the pressures on aerodynamic shapes at very high supersonic speeds in dense air with the ratio of specific heats equal to 1. The method is applicable to any body of revolution at zero angle of attack and to any two-dimensional profile. The results of the present paper are compared with previous work of Von Karman and Epstein on this problem and the difference explained.
Author:
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ISBN:
Category :
Languages : en
Pages : 50
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In a previous paper (AD-296 177), the transversal contour of a slender body of a given length and base area was determined in such a way that the total drag (sum of the pressure drag and the friction drag) is a minimum. Directions were employed, and the analysis was confined to a body whose cross section is either a regular polygon or is composed of a basic circle external to which are superimposed symmetric segments of a logarithmic spiral. In this paper, these arbitrary limitations on the transversal contour are removed, and the minimum drag problem is investigated with the indirect methods of the Calculus of Variations. The following basic hypotheses are employed: (a) the body is slender in the longitudinal sense; (b) its longitudinal contour is represented by a power law; (c) the distribution of pressure coefficients is Newtonian; and (d) the distribution of skin friction coefficients versus the abscissa is represented by a power law.
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 428
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Book Description
