On the Calculation of Unsteady Nonlinear Three-dimensional Supersonic Flow Past Wings PDF Download
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Author: Stanford University. Department of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 106
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Book Description
A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).
Author: Stanford University. Department of Aeronautics and Astronautics
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 106
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Book Description
A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).
Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 216
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Book Description
Author: Chong-Wei Chu
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
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Book Description
Author: Chong-Wei Chu
Publisher:
ISBN:
Category :
Languages : en
Pages : 205
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Book Description
I ;Powers, Sidney A. ;NOR-72-87-Vol-2F33615-72-C-1429AF-1366AFFDLTR-72-91-Vol-2See also Volume 1, AD-753 695.(*airframes, *supersonic characteristics), (*computer programs, aerodynamics), numerical analysis, conical bodies, delta wings, instruction manuals, blunt bodies, hypersonic characteristics, angle of attack, three dimensional flow, subroutinescomputer aided analysis, smooth bodies, inviscid flowThe report describes the theories, the numerical methods and the computer programs developed for determining the inviscid three-dimensional flow about smooth shapes at supersonic speeds. Volume II is a user's manual for the computer programs and provides the detailed information needed to set up and use the programs. These programs can determine the supersonic flow past smooth blunted bodies for any angle of attack for which the initial value surface remains on the blunted nose. The lowest usable Mach number is on the order of 2.0, with lower values attainable by careful attention to the initial value surface solution. There is no computational upper limit on the Mach number. (Author).
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
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Book Description
In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 89
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Book Description
The report describes the theories, the numerical methods and the computer programs developed for determining the inviscid three- dimensional flow about smooth shapes at supersonic speeds. Volume 1 describes the theoretical and numerical approaches and compares two sample cases with experiment; a blunted 15 deg cone at 20 deg angle of attack in helium at M = 14. 9, and a 70 deg slab delta wing at 15 deg angle of attack in air at M = 9.6. The numerical results are in close agreement with the experimental data.
Author: Maurice Holt
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 78
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
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Author: S. Y. Ruo
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 60
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Book Description
An analytical approach is presented to account for some of the nonlinear characteristics of the transonic flow equation for finite thickness wings undergoing harmonic oscillation at sonic flight speed in an inviscid, shock-free fluid. The thickness effect is accounted for in the analysis through use of the steady local Mach number distribution over the wing at its mean position by employing the local linearization concept and a coordinate transformation. Computed results are compared with that of the linearized theory and experiments. Based on the local linearization concept, an alternate formulation avoiding the limitations of the coordinate transformation method is presented.
Author: John V. Rakich
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
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Book Description
Characteristics method for determining three dimensional supersonic flow around inclined body of revolution.
