Author: Dean R. Chapman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 852
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
Author: Dean R. Chapman
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 852
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.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 852
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
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
Book Description
NASA Technical Note
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 686
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 686
Book Description
Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 48
Book Description
Afterbody Pressures on Two-dimensional Boattailed Bodies Having Turbulent Boundary Layers at Mach 5.98
Author: W. Frank Staylor
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 48
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 48
Book Description
Annual Report
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 534
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1200
Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Research Memorandum
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 70
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 70
Book Description
Aerodynamics of Guided and Unguided Weapons
Author: Frankie Gale Moore
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 218
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.
Publisher:
ISBN:
Category : Guided missiles
Languages : en
Pages : 218
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
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 540
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 540
Book Description