Influence of Non-Adiabatic Model Surface on Transition Measurements Using the Temperature-Sensitive Paint technique in a cryogenic wind tunnel-Reference-Cited by-同舟云学术

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Influence of Non-Adiabatic Model Surface on Transition Measurements Using the Temperature-Sensitive Paint technique in a cryogenic wind tunnel

Published:2012-06-25 Issue: Volume: Page:
ISSN:
Container-title:42nd AIAA Fluid Dynamics Conference and Exhibit
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Author:

Costantini Marco¹,Fey Uwe¹,Henne Ulrich¹,Klein Christian¹

Affiliation:

1. German Aerospace Center (DLR)

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.2012-2830

Reference43 articles.

1. 1Lees,L."TheStabilityoftheLaminarBoundaryLayerinCompressibleFluid",NACAReport876,1947.

2. 3Lees,L.,andLin,C.C."InvestigationoftheStabilityoftheLaminarBoundaryLayerinaCompressibleFluid,"NACATN 1115,1946.

3. Drag Reduction by Cooling in Hydrogen-Fueled Aircraft

4. 5Reshotko,E."Controlofboundary-layertransition,"AIAAPaperNo.1985-0562.

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