Author: Benjamin Robert Smith
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 290
Book Description
Mean Flow Measurements of Heated Supersonic Slot Injection Into a High Reynolds Number Supersonic Stream
Author: Benjamin Robert Smith
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 290
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 290
Book Description
Turbulence Measurements of Heated Supersonic Slot Injection Into a Supersonic Stream
Author: Camillus Randolph Hyde
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 338
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 338
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.
AIAA 28th Aerospace Sciences Meeting
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 458
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 458
Book Description
Supersonic Flow Calculation Using a Reynolds-stress and an Eddy Thermal Diffusivity Turbulence Model
Author: T. P. Sommer
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 44
Book Description
Aeronautical Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 712
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 712
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Mean-flow Measurements of a Turbulent Mixing Layer from Helium Slot Injection Into a Supersonic Airstream
Author: Fei Thomas Kwok
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 398
Book Description
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 398
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1108
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1108
Book Description
Supersonic Flow Calculation Using a Reynolds-Stress and an Eddy Thermal Diffusivity Turbulence Model
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722829797
Category :
Languages : en
Pages : 42
Book Description
A second-order model for the velocity field and a two-equation model for the temperature field are used to calculate supersonic boundary layers assuming negligible real gas effects. The modeled equations are formulated on the basis of an incompressible assumption and then extended to supersonic flows by invoking Morkovin's hypothesis, which proposes that compressibility effects are completely accounted for by mean density variations alone. In order to calculate the near-wall flow accurately, correction functions are proposed to render the modeled equations asymptotically consistent with the behavior of the exact equations near a wall and, at the same time, display the proper dependence on the molecular Prandtl number. Thus formulated, the near-wall second order turbulence model for heat transfer is applicable to supersonic flows with different Prandtl numbers. The model is validated against flows with different Prandtl numbers and supersonic flows with free-stream Mach numbers as high as 10 and wall temperature ratios as low as 0.3. Among the flow cases considered, the momentum thickness Reynolds number varies from approximately 4,000 to approximately 21,000. Good correlation with measurements of mean velocity, temperature, and its variance is obtained. Discernible improvements in the law-of-the-wall are observed, especially in the range where the big-law applies. Sommer, T. P. and So, R. M. C. and Zhang, H. S. Unspecified Center NAG1-1080; RTOP 505-70-59-08...
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722829797
Category :
Languages : en
Pages : 42
Book Description
A second-order model for the velocity field and a two-equation model for the temperature field are used to calculate supersonic boundary layers assuming negligible real gas effects. The modeled equations are formulated on the basis of an incompressible assumption and then extended to supersonic flows by invoking Morkovin's hypothesis, which proposes that compressibility effects are completely accounted for by mean density variations alone. In order to calculate the near-wall flow accurately, correction functions are proposed to render the modeled equations asymptotically consistent with the behavior of the exact equations near a wall and, at the same time, display the proper dependence on the molecular Prandtl number. Thus formulated, the near-wall second order turbulence model for heat transfer is applicable to supersonic flows with different Prandtl numbers. The model is validated against flows with different Prandtl numbers and supersonic flows with free-stream Mach numbers as high as 10 and wall temperature ratios as low as 0.3. Among the flow cases considered, the momentum thickness Reynolds number varies from approximately 4,000 to approximately 21,000. Good correlation with measurements of mean velocity, temperature, and its variance is obtained. Discernible improvements in the law-of-the-wall are observed, especially in the range where the big-law applies. Sommer, T. P. and So, R. M. C. and Zhang, H. S. Unspecified Center NAG1-1080; RTOP 505-70-59-08...
NASA Scientific and Technical Reports
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 428
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 428
Book Description