Author: Sheryll Goecke Powers
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 46
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 Powers
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 46
Book Description
Publisher:
ISBN:
Category : Drag (Aerodynamics)
Languages : en
Pages : 46
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...
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...
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
Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing
Author: John A. Zalovcik
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 26
Book Description
Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 26
Book Description
Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.
Aircraft Excrescence Drag
Author: Alec David Young
Publisher:
ISBN: 9789283513926
Category : Boundary layer
Languages : en
Pages : 159
Book Description
Publisher:
ISBN: 9789283513926
Category : Boundary layer
Languages : en
Pages : 159
Book Description
Wing Pressure Distribution and Boundary Layer Data Obtained from C-5A Flight Testing
A Comparison at Mach Numbers Up to 0.92 of the Calculated and Experimental Downwash and Wake Characteristics at Various Horizonatl Tail Heights Behind a Wing with 45 Degrees of Sweepback
Author: Jack D. Stephenson
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 86
Book Description
Handbook of Supersonic Aerodynamics
Author: Johns Hopkins University. Applied Physics Laboratory, Silver Spring, Md
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 516
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 516
Book Description
Handbook of Hydraulic Resistance
Author: I. E. Idelchik
Publisher:
ISBN: 9788179921180
Category : Fluid dynamics
Languages : en
Pages : 0
Book Description
The handbook has been composed on the basis of processing, systematization and classification of the results of a great number of investigations published at different time. The essential part of the book is the outcome of investigations carried out by the author. The present edition of this handbook should assist in increasing the quality and efficiency of the design and usage of indutrial power engineering and other constructions and also of the devices and apparatus through which liquids and gases move.
Publisher:
ISBN: 9788179921180
Category : Fluid dynamics
Languages : en
Pages : 0
Book Description
The handbook has been composed on the basis of processing, systematization and classification of the results of a great number of investigations published at different time. The essential part of the book is the outcome of investigations carried out by the author. The present edition of this handbook should assist in increasing the quality and efficiency of the design and usage of indutrial power engineering and other constructions and also of the devices and apparatus through which liquids and gases move.