Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities

Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities PDF Author: Dean R. Chapman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 852

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Book Description
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.

Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities

Experimental Investigation Base Pressure on Blunt-trailing-edge Wings at Supersonic Velocities PDF Author: Dean R. Chapman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 852

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Book Description
The pressres acting on the base of blunt-trailing-edge airfoils have been measured at Mach numbers of 1.25, 1.5, 2.0, and 3.1 and at Reynolds numbers from 0.2 to 3.8 million. Data are presented for 29 profiles both with laminar and with turbulent boundary layers approaching the trailing edges of the wings. The base pressure is found to be a function primarily of Mach number and the ratio of the boundary layer thickeness at the trailing edge to the trailing-edge thickness.

Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026

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NASA Technical Note

NASA Technical Note PDF Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 686

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Report

Report PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 48

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Afterbody Pressures on Two-dimensional Boattailed Bodies Having Turbulent Boundary Layers at Mach 5.98

Afterbody Pressures on Two-dimensional Boattailed Bodies Having Turbulent Boundary Layers at Mach 5.98 PDF Author: W. Frank Staylor
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 48

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Annual Report

Annual Report PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534

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Annual Report of the National Advisory Committee for Aeronautics

Annual Report of the National Advisory Committee for Aeronautics PDF 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.

Research Memorandum

Research Memorandum PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 70

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Aerodynamics of Guided and Unguided Weapons

Aerodynamics of Guided and Unguided Weapons PDF Author: Frankie Gale Moore
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 218

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Book Description
Several theoretical and empirical procedures are combined into a single computer program to predict lift, drag, and center of pressure on quite general wing-body geometries. The method is applicable for Mach number zero to three and angle-of-attack zero to about fifteen degrees. Computed results for several configurations compare well with experimental and other analytical results. It costs about five dollars per Mach number to compute the static aerodynamics of a typical wing-body shape on the CDC 6700 computer.

Technical Note

Technical Note PDF Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 540

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