Calculative Techniques for Transonic Flows about Certain Classes of Wing-body Combinations: Phase II PDF Download
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Author: Stephen S. Stahara
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages :
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Book Description
Author: Stephen S. Stahara
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages :
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Book Description
Author: S. S. Stahara
Publisher:
ISBN:
Category :
Languages : en
Pages : 122
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Book Description
Theoretical analysis and associated computer programs were developed for predicting properties of transonic flows about certain classes of wing-body combinations. The procedures used are based on the transonic equivalence rule and employ either an arbitrarily-specified solution or the local linerization method for determining the nonlifting transonic flow about the equivalent body. The class of wind planform shapes include wings having sweptback trailing edges and finite tip chord. Theoretical results are presented for surface and flow-field pressure distributions for both nonlifting and lifting situations at Mach number one.
Author: Stephen S. Stahara
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 108
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Author: Stephen S. Stahara
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 118
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Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 154
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Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 936
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Author: Richard W. Barnwell
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 116
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Book Description
The three-dimensional problem of transonic flow about lifting wing-body configurations is reduced to a two-variable computational problem with the method of matched asymptotic expansions. The computational problem is solved with the method of relaxation. The method accounts for leading-edge separation, the presence of shock waves, and the presence of solid, slotted, or porous tunnel walls. The Mach number range of the method extends from zero to the supersonic value at which the wing leading edge becomes sonic. A modified form of the transonic area rule which accounts for the effect of lift is developed. This effect is explained from simple physical considerations.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 562
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1282
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Book Description
February issue includes Appendix entitled Directory of United States Government periodicals and subscription publications; September issue includes List of depository libraries; June and December issues include semiannual index
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 558
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