Supersonic wind tunnel diffuser performance with high model blockageat moderate to low Reynolds numbers-Reference-Cited by-同舟云学术

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Supersonic wind tunnel diffuser performance with high model blockageat moderate to low Reynolds numbers

Published:1991-06-24 Issue: Volume: Page:
ISSN:
Container-title:27th Joint Propulsion Conference
language:
Short-container-title:

Author:

HANUS G.¹,MIKKELSEN K.¹,OLSTAD S.¹,CARISTIA S.²

Affiliation:

1. Fluidyne Engineering Corp., Minneapolis, MN

2. Centro Italiano Ricerche Aerospaziali, Naples, Italy

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1991-2274

Reference10 articles.

1. tion of Fixed-Geometry Diffusers in an Open-Jet Wind Tunnel at Mach Numbers Between 14 and 18andReynoldsNumbers between 8,900 and 25,000," AEDCTR-67-3,March, 1967. [3] Boylan, D.E. "An Experimental Study of

2. TDR-64-47, April, 1964. [41 Smith,R.T. "ExperimentalStudiesofHigh

Cited by 4 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. Numerical Analysis of an Actively Cooled Low-Reynolds-Number Hypersonic Diffuser;Journal of Thermophysics and Heat Transfer;2019-01

2. The Effect of Diffuser Geometry on the Starting Pressure Ratio of a Supersonic Wind Tunnel;27th AIAA Aerodynamic Measurement Technology and Ground Testing Conference;2010-06-28

3. Low-Reynolds number supersonic diffuser for a plasma-heated wind tunnel;International Journal of Thermal Sciences;2001-10

4. An overview of the planned aerospace test facilities at Capua, Italy;28th Joint Propulsion Conference and Exhibit;1992-07-06

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