Author: Sheryll A. GoeckePublisher:
ISBN:
Category :
Languages : en
Pages : 31
Book Description
Flight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an AFT-facing Step for Mach Numbers from 0.4 to 2.5/ by Sheryll A. Goecke
Author: Sheryll A. GoeckeFlight-measured Base Pressure Coefficients for Thick Boundary-layer Flow Over an Aft-facing Step for Mach Numbers from 0.4 to 2.5
Author: Sheryll A. GoeckePublisher:
ISBN:
Category : B-70 bomber
Languages : en
Pages : 44
Book Description
Flight-measured Pressure Characteristics of Aft-facing Steps in High Reynolds Number Flow at Mach Numbers of 2.20, 2.50, and 2.80 and Comparison with Other Data
Author: Sheryll Goecke PowersPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 44
Book Description
Flight-measured pressure characteristics of aft-facing steps in high Reynolds number flow at Mach numbers of 2.20, 2.50, and 2.80 and comparison with other data
Author: Sheryll Goecke PowersPublisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 46
Book Description
Scientific and Technical Aerospace Reports
Author: Flight-Measured Pressure Characteristics of Aft-Facing Steps in High Reynolds Number Flow at Mach Numbers of 2.20, 2.50, and 2.80 and Comparison with Other Data
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781726013260
Category :
Languages : en
Pages : 38
Book Description
The YF-12 airplane was studied to determine the pressure characteristics associated with an aft-facing step in high Reynolds number flow for nominal Mach numbers of 2.20, 2.50, and 2.80. Base pressure coefficients were obtained for three step heights. The surface static pressures ahead of and behind the step were measured for the no-step condition and for each of the step heights. A boundary layer rake was used to determine the local boundary layer conditions. The Reynolds number based on the length of flow ahead of the step was approximately 10 to the 8th power and the ratios of momentum thickness to step height ranged from 0.2 to 1.0. Base pressure coefficients were compared with other available data at similar Mach numbers and at ratios of momentum thickness to step height near 1.0. In addition, the data were compared with base pressure coefficients calculated by a semiempirical prediction method. The base pressure ratios are shown to be a function of Reynolds number based on momentum thickness. Profiles of the surface pressures ahead of and behind the step and the local boundary layer conditions are also presented. Powers, S. G. Armstrong Flight Research Center NASA-TM-72855, H-956 RTOP 505-06-34...
AGARD Conference Proceedings
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and DevelopmentPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1232
Book Description
STAR
Author: Government Reports Index
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1080
Book Description
Author: