Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 342
Book Description
Technical Note
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 342
Book Description
Investigation at Supersonic Speeds of the Variation with Reynolds Number and Mach Number of the Total, Base, and Skin-friction Drag of Seven Boattail Bodies of Revolution Designed for Minimum Wave Drag
Author: August F. BrommPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 26
Book Description
Pressure Distributions on Three Bodies of Revolution to Determine the Effect of Reynolds Number Up to and Including the Transonic Speed Range
Author: John M. SwihartPublisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 46
Book Description
Abstract: The effects of varying Reynolds number on the pressure distribution over a transonic body of revolution are presented. Angles of attack from -2° to 15° were investigated through a Mach number range from 0.60 to 1.09. The Reynolds number based on body length varied from 9 x 106 to 39 x 106, and on maximum diameter from 1.35 x 105 to 4.53 x 105. There were small effects of Reynolds number on the axial pressure distributions of these bodies. These effects were of such a nature as to cause an increase of 0.05 in the normal-force coefficient of the body when tested in the subcritical cross-flow Reynolds number range. A comparison between values of incremental pressure coefficient due to angle of attack and theoretical values was made.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 878
Book Description
Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel
Author: Donald E. ColettiPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
Book Description
Index of NACA Technical Publications
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
Book Description
Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8
Author: Davis H. CrawfordPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 680
Book Description
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
NACA Research Memorandum
Author: Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 72
Book Description
A Selected Listing of NASA Scientific and Technical Reports for ...
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 818
Book Description
Investigations at Supersonic Speeds of the Base Pressure on Bodies of Revolution with and Without Sweptback Stabilizing Fins
Author: Eugene S. LovePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70
Book Description
