Stagnation Temperature Measurements in a Hypersonic Wind-Tunnel using the Sodium Line Reversal Method

Nature ◽  
1961 ◽  
Vol 190 (4778) ◽  
pp. 778-779 ◽  
Author(s):  
J. L. STOLLERY
Keyword(s):  
Wind Tunnel ◽  
Temperature Measurements ◽  
Stagnation Temperature ◽  
Hypersonic Wind Tunnel

DETERMINATION OF MATERIAL CATALYCITY AT HIGH TEMPERATURES IN THE VAT-104 HYPERSONIC WIND TUNNEL

2014 ◽  
Vol 45 (1) ◽  
pp. 3-20 ◽  
Author(s):  
Ivan Vladimirovich Egorov ◽  
Boris Evgen'evich Zhestkov ◽  
Vladimir Viktorovich Shvedchenko
Keyword(s):  
Wind Tunnel ◽  
High Temperatures ◽  
Hypersonic Wind Tunnel

scholarly journals An overview of X-38 Hypersonic Wind Tunnel data and comparison with numerical results

1997 ◽  
Author(s):  
Charles Campbell ◽  
Jose Caram ◽  
Scott Berry ◽  
Michael DiFulvio ◽  
Tom Horvath ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Numerical Results ◽  
Hypersonic Wind Tunnel ◽  
Wind Tunnel Data

Electron beam-driven MHD for the RDHWT/MARIAH II hypersonic wind tunnel

2000 ◽  
Author(s):  
Gloyd Simmons ◽  
Gordon Nelson ◽  
Jean-Luc Cambier ◽  
Sergey Macheret ◽  
Mikhail Shneider ◽  
...  
Keyword(s):  
Electron Beam ◽  
Wind Tunnel ◽  
Hypersonic Wind Tunnel

scholarly journals Hypersonic Free Flight Investigation on Rudder Reflection of Aircraft

Proceedings ◽  
2018 ◽  
Vol 2 (8) ◽  
pp. 542
Author(s):  
Fei Xue ◽  
Yuchao Wang ◽  
Zenghui Jiang ◽  
Yinong Yang
Keyword(s):  
Wind Tunnel ◽  
Degrees Of Freedom ◽  
Wind Tunnel Test ◽  
Model Matching ◽  
Free Flight ◽  
Control Effect ◽  
Time Curve ◽  
Hypersonic Wind Tunnel ◽  
Before And After ◽  
Ejection Mechanism

In order to study the control effect of the rudder surface of the hypersonic vehicle and the coupling dynamic characteristics of the rudder surface deflection and the flight attitude, a technical platform for the deflection and motion coupling of the aircraft rudder surface was designed. The platform ejection mechanism can launch the model into the wind tunnel flow field according to the preset attitude, and model can free flight without support interference. The innovative design of the model internal rudder partial system can guarantee the model to deflect the rudder surface in the free flight process, simulate the real steering process of the aircraft. By changing spring with different springs, the speed of the rudder surface can be changed. The dual optical path and image acquisition technology can capture the motion picture before and after the deflection of the rudder surface from two angles. After the image is matched by model matching, the six degrees of freedom parameter of the model can be changed with the time curve before and after the deflection of the rudder surface, and the area of the six freedom degree curve of the different state model is compared. In other words, the specific influence of dynamic rudder rotation on the motion of the model is known. The wind tunnel test of the model in the hypersonic wind tunnel of the 500 mm is carried out using this platform. The test results are highly repeatable, and the test platform technology is mature and reliable.

scholarly journals Nonintrusive Freestream Velocity Measurement in a Large-Scale Hypersonic Wind Tunnel

AIAA Journal ◽  
2017 ◽  
Vol 55 (10) ◽  
pp. 3611-3616 ◽  
Author(s):  
M. A. Mustafa ◽  
N. J. Parziale ◽  
M. S. Smith ◽  
E. C. Marineau
Keyword(s):  
Wind Tunnel ◽  
Velocity Measurement ◽  
Large Scale ◽  
Freestream Velocity ◽  
Hypersonic Wind Tunnel
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