Generalization of Boundary-layer Momentum-integral Equations to Three-dimensional Flows Including Those of Rotating System PDF Download
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Author: Artur Mager
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 47
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Book Description
A numerical evaluation of this solution carried out the data obtained in a curving nonrotating duct shows a fair quantitative agreement with the measured values.
Author: Artur Mager
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 47
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Book Description
A numerical evaluation of this solution carried out the data obtained in a curving nonrotating duct shows a fair quantitative agreement with the measured values.
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1462
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
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Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author: Roberto Vaglio-Laurin
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 54
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Book Description
Author: Arthur W. Goldstein
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 236
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 620
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1274
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Book Description
Author: Stanley Faber
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 680
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Book Description
In this study in which an airplane simulator with one degree of freedom (pitch) was used, results were determined for three conditions of airplane dynamics. For an undamped natural frequency of 1/2 cps with a damping ratio of 0.18 and for an undamped natural frequency of 1 cps with a damping ratio of 0.11, moderate longitudinal stick forces and displacements were desired.
Author: Maurice Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 686
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Book Description
An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
