Author: Ralph C. Tolle
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 274
Book Description
Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects
Author: Ralph C. Tolle
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 274
Book Description
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 274
Book Description
Development and Testing of a New Optimum Design Code for Hypersonic Wind Tunnel Nozzles, Including Boundary Layer, Turbulence, and Real Gas Effects
Author: Ralph C. Tolle
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 241
Book Description
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 241
Book Description
35th Aerospace Sciences Meeting & Exhibit
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 780
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 780
Book Description
Government Reports Announcements & Index
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 676
Book Description
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 676
Book Description
American Doctoral Dissertations
Author:
Publisher:
ISBN:
Category : Dissertation abstracts
Languages : en
Pages : 896
Book Description
Publisher:
ISBN:
Category : Dissertation abstracts
Languages : en
Pages : 896
Book Description
Scientific and Technical Aerospace Reports
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 704
Book Description
Fluid Flow Analysis of a Hot-core Hypersonic-wind-tunnel Nozzle Concept
Author: John B. Anders
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 36
Book Description
A hypersonic-wind-tunnel nozzle concept which incorporates a hot-core flow surrounded by an annular flow of cold air offers a promising technique for maximizing the model size while minimizing the power required to heat the test core. This capability becomes especially important when providing the true-temperature duplication needed for hypersonic propulsion testing. Several two-dimensional wind-tunnel nozzle configurations that are designed according to this concept are analyzed by using recently developed analytical techniques for prediction of the boundary-layer growth and the mixing between the hot and cold coaxial supersonic airflows. The analyses indicate that introduction of the cold annular flow near the throat results in an unacceptable test core for the nozzle size and stagnation conditions considered because of both mixing and condensation effects. Use of a half-nozzle with a ramp on the flat portion does not appear promising because of the thick boundary layer associated with the extra length. However, the analyses indicate that if the cold annular flow is introduced at the exit of a full two-dimensional nozzle, an acceptable test core will be produced. Predictions of the mixing between the hot and cold supersonic streams for this configuration show that mixing effects from the cold flow do not appreciably penetrate into the hot core for the large downstream distances of interest.
The Effect of the Boundary Layer Upon the Flow in a Conical Hypersonic Wind Tunnel Nozzle
Author: Martin Sichel
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
Publisher:
ISBN:
Category :
Languages : en
Pages : 84
Book Description
NOL Hypervelocity Wind Tunnel
Author: Naval Ordnance Laboratory (White Oak, Md.).
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 154
Book Description
Publisher:
ISBN:
Category : Hypersonic wind tunnels
Languages : en
Pages : 154
Book Description
Aeronautical Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
Book Description