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
AGARD Conference Proceedings
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and DevelopmentPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1232
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: 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...
Effect of Leading-edge Thickness on the Flow Over a Flat Plate at a Mach Number of 5.7
Author: Marcus O. CreagerPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
Simplified Method for Determination of Critical Height of Distributed Roughness for Boundary-layer Transition at Mach Numbers from 0 to 5
Author: Albert L. BraslowPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 624
Book Description
The method has been applied to various types of configurations in several wind-tunnel investigations conducted by the National Advisory Committee for Aeronautics at Mach numbers up to 4, and in all cases the calculated roughness height caused premature boundary-layer transition for the range of test conditions.
Boundary-layer Measurements in Accelerated Flows Near Mach 1
Author: Howard L. WesokyPublisher:
ISBN:
Category : Axial flow
Languages : en
Pages : 40
Book Description
High Speed Flow Separation Ahead of Finite Span Steps
Author: Louis G. KaufmanPublisher:
ISBN:
Category : Turbulence
Languages : en
Pages : 80
Book Description
Detailed surface heat transfer data, oil flow, and schlieren photographs are presented for high speed flow separation ahead of finite span, forward facing steps on flat plates. Step spans were varied from three to ten times as large as the step height, and the step heights are three to four times larger than the undisturbed turbulent boundary layer thickness. Reynolds numbers, based on plate length, were approximately 15 million for both Mach 4.75 and Mach 5.04 local undisturbed flows over the flat plate surface. For these test conditions, the maximum extent of separation ahead of the step is approximately 4.4 times as large as the step height independent of step span, and peak heating rates were measured that are more than six to eight times larger than the undisturbed flow heating rates. Peak heating on the plate surface occurs slightly upstream and approximately 1/2 step height inboard of the outboard sides of the steps; the increase in peak heat transfer coefficients over the undisturbed flow values decreases with increasing step span. In addition to presenting the detailed surface heat transfer data, a plausible theoretical analysis is presented for calculating the region of turbulent boundary layer separation ahead of these finite span steps.