Author: David Preston Lewis
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Tangential Supersonic Slot Injection Into a Supersonic Stream with a Simulated Near-separation Initial Boundary Layer
Author: David Preston Lewis
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 90
Book Description
An Experimental Study of Slot Injection Into a Supersonic Stream
Author: Michael Kenworthy
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
An experimental investigation of two-dimensional tangential-slot injection into a turbulent boundary layer at a freestream Mach number of 2.4 has been conducted. Nearly adiabatic surface temperatures were maintained during all tests. Static and pitot pressure profiles at four stations downstream of the slot were obtained. Skin friction was measured at the last three stations with a self-nulling balance. Schlieren photographs of the flow field were also obtained. Most of the data were obtained with slot Mach numbers of 0.31 and 0.66 corresponding to slot pressure less than and equal to stream static pressure, respectively. For the latter matched-pressure case, tangential slot injection reduced the surface shear at the three measuring stations by about 60 to 20 percent for increasing downstream distances from the slot of 12 to 28 slot heights. However, for the other case where slot pressure was less than stream static pressure, the effect of injection was to increase the shear by about 90 percent at the last downstream station of 28 slot heights. This increase in shear is attributed to the rapid acceleration of the low speed injectant stream by the high speed main stream and the increasing pressure through the recompression zone which is absent for the matched pressure case.
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 52
Book Description
An experimental investigation of two-dimensional tangential-slot injection into a turbulent boundary layer at a freestream Mach number of 2.4 has been conducted. Nearly adiabatic surface temperatures were maintained during all tests. Static and pitot pressure profiles at four stations downstream of the slot were obtained. Skin friction was measured at the last three stations with a self-nulling balance. Schlieren photographs of the flow field were also obtained. Most of the data were obtained with slot Mach numbers of 0.31 and 0.66 corresponding to slot pressure less than and equal to stream static pressure, respectively. For the latter matched-pressure case, tangential slot injection reduced the surface shear at the three measuring stations by about 60 to 20 percent for increasing downstream distances from the slot of 12 to 28 slot heights. However, for the other case where slot pressure was less than stream static pressure, the effect of injection was to increase the shear by about 90 percent at the last downstream station of 28 slot heights. This increase in shear is attributed to the rapid acceleration of the low speed injectant stream by the high speed main stream and the increasing pressure through the recompression zone which is absent for the matched pressure case.
Masters Theses and Doctoral Dissertations in the Pure and Applied Sciences Accepted by Colleges and Universities of the United States
Author:
Publisher:
ISBN:
Category : Chemistry
Languages : en
Pages : 544
Book Description
Publisher:
ISBN:
Category : Chemistry
Languages : en
Pages : 544
Book Description
Master's Theses and Doctoral Dissertations in the Pure and Applied Sciences
Author:
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 186
Book Description
Publisher:
ISBN:
Category : Dissertations, Academic
Languages : en
Pages : 186
Book Description
RESEARCH ON SLOT INJECTION INTO A SUPERSONIC AIR STREAM.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 111
Book Description
The results of an experimental and analytical study of tangential slot injection into a supersonic stream are presented. The experiments were performed in an atmospheric intake wind tunnel with freestream Mach numbers of 2.85 and 4.19. Injection of air, helium and carbon dioxide at various subsonic Mach numbers and one supersonic condition was considered. Experiments for the flow over of wedges with turning angles between 5 and 25 deg. located on the wall downstream of the injection are also reported. The principal data are in the form of spark schlieren photographs, interferograms and wall static pressure distributions. Density profiles at several axial stations determined from interferograms are also presented. The transition to turbulence in the shear layer and the character of the turbulence were observed from the spark schlieren photographs. The presence of separation zones was detected by small tufts or threads on the surface. With subsonic injection, it is found that the initial slot exit conditions are not arbitrary for a given injectant mass flow but are determined by the downstream interaction between the two streams. The flow field has many of the features of the now well-known base-flow problem. A relatively simple analysis is developed which predicts the initial jet exit conditions. Very good agreement with the experimental observations is achieved.
Publisher:
ISBN:
Category :
Languages : en
Pages : 111
Book Description
The results of an experimental and analytical study of tangential slot injection into a supersonic stream are presented. The experiments were performed in an atmospheric intake wind tunnel with freestream Mach numbers of 2.85 and 4.19. Injection of air, helium and carbon dioxide at various subsonic Mach numbers and one supersonic condition was considered. Experiments for the flow over of wedges with turning angles between 5 and 25 deg. located on the wall downstream of the injection are also reported. The principal data are in the form of spark schlieren photographs, interferograms and wall static pressure distributions. Density profiles at several axial stations determined from interferograms are also presented. The transition to turbulence in the shear layer and the character of the turbulence were observed from the spark schlieren photographs. The presence of separation zones was detected by small tufts or threads on the surface. With subsonic injection, it is found that the initial slot exit conditions are not arbitrary for a given injectant mass flow but are determined by the downstream interaction between the two streams. The flow field has many of the features of the now well-known base-flow problem. A relatively simple analysis is developed which predicts the initial jet exit conditions. Very good agreement with the experimental observations is achieved.
Supersonic Turbulent Boundary-layer Flows with Tangential Slot Injection
Author: E. W. Miner
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Evaluation of a Technique to Generate Artificially Thickened Boundary Layers in Supersonic and Hypersonic Flows
Author: A. R. Porro
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Evaluation of a Technique to Generate Artificially Thickened Boundary Layers in Supersonic and Hypersonic Flows
Author:
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
Numerical Simulation of Slot Injection Into a Turbulent Supersonic Stream
Author: Donald P. Rizzetta
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
32nd Thermophysics Conference
Author:
Publisher:
ISBN:
Category : Thermodynamics
Languages : en
Pages : 562
Book Description
Publisher:
ISBN:
Category : Thermodynamics
Languages : en
Pages : 562
Book Description