scholarly journals Improvement of a sensitivity-adjustable three component force balance and its application to supersonic wind tunnel testing

2014 ◽  
Vol 9 (5) ◽  
pp. JFST0068-JFST0068
Author(s):  
Gouji YAMADA ◽  
Shingo IMAGAWA ◽  
Katuyuki INOUE ◽  
Hiromitsu KAWAZOE ◽  
Shigeru OBAYASHI
Keyword(s):  
Wind Tunnel ◽  
Force Balance ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Component Force ◽  
Tunnel Testing

scholarly journals Development of a Sensitivity-Adjustable Three-Component Force Balance and Its Application to Wind Tunnel Testing

2013 ◽  
Vol 8 (2) ◽  
pp. 209-218 ◽  
Author(s):  
Gouji YAMADA ◽  
Hiromitsu KAWAZOE ◽  
Hiroshi SUEMURA ◽  
Takashi MATSUNO ◽  
Shigeru OBAYASHI
Keyword(s):  
Wind Tunnel ◽  
Force Balance ◽  
Wind Tunnel Testing ◽  
Component Force ◽  
Tunnel Testing

Design, modelling and analysis of a six component force balance for hypervelocity wind tunnel testing

2001 ◽  
Vol 79 (11) ◽  
pp. 1077-1088 ◽  
Author(s):  
A.L. Smith ◽  
D.J. Mee ◽  
W.J.T. Daniel ◽  
T. Shimoda
Keyword(s):  
Wind Tunnel ◽  
Force Balance ◽  
Wind Tunnel Testing ◽  
Component Force ◽  
Tunnel Testing

Videogrammetry and its Application on Attack Angle Measuring in Wind Tunnel Testing

2012 ◽  
Vol 588-589 ◽  
pp. 1050-1053
Author(s):  
Xu Hui Huang ◽  
Zheng Yu Zhang
Keyword(s):  
Wind Tunnel ◽  
Measurement System ◽  
Attack Angle ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Angle Measuring ◽  
Tunnel Testing

The videogrammetric measurement is a favorite technology in wind tunnel testing, because it neither destroys the model’s shape, nor changes the stiffness or strength. In this paper, a videogrammetric measurement system(VMS) is introduced, and it is used to measure model’s attack angle. Three engineering videogrammetric experiments of attack angle in 2 meter supersonic wind tunnel testing have demonstrated that the precision of VMS established by this paper is ≤0.0094°, so it is useful and effective.

Design of Subscale Parachute Models for MSL Supersonic Wind Tunnel Testing

2009 ◽  
Author(s):  
Allen Witkowski ◽  
Mike Kandis ◽  
James Reuter ◽  
Walter Machalick ◽  
Richard Kelsch ◽  
...  
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Tunnel Testing

Videogrammetry of the Model’s Attitude in Wind Tunnel Testing

2012 ◽  
Vol 190-191 ◽  
pp. 1273-1277 ◽  
Author(s):  
Zheng Yu Zhang ◽  
Zhong Xiang Sun ◽  
Xu Hui Huang ◽  
Yan Sun
Keyword(s):  
Standard Deviation ◽  
Wind Tunnel ◽  
Drag Coefficient ◽  
Systematic Error ◽  
Measurement System ◽  
High Speed ◽  
Wind Tunnel Test ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Tunnel Testing

The advanced precision of drag coefficient is 0.0001 for the high speed wind tunnel test of measuring forces, the model’s angle of attack precision is ≤0.01°following errors distribution. A videogrammetric method of model’s attitude is therefore proposed, its uncertainty is investigated, and a compensation method of its systematic error is also presented by this paper. The three engineering videogrammetric experiments of attack angle in 2 meter supersonic wind tunnel testing have demonstrated that measuring standard deviation of videogrammetric measurement system established by this paper is ≤0.0094°, in addition it neither destroys the model’s shape, nor changes the stiffness or strength, so it is useful and effective.

Uncertainty Identification of Supersonic Wind-Tunnel Testing

2011 ◽  
Vol 48 (2) ◽  
pp. 567-577 ◽  
Author(s):  
Shinji Nagai ◽  
Hidetoshi Iijima
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Tunnel Testing

Some Factors Involved in the Supersonic Wind Tunnel Testing of Models

1958 ◽  
Vol 62 (576) ◽  
pp. 893-897
Author(s):  
P. A. Champion
Keyword(s):  
Wind Tunnel ◽  
Wind Tunnel Testing ◽  
Supersonic Wind Tunnel ◽  
Supersonic Flight ◽  
Common Experience ◽  
Use Of Models ◽  
Tunnel Testing

The use of models in the determination of aircraft behaviour is as old as flying itself, and wind tunnel models in particular have played a very important part. Now that supersonic flight of aircraft and missiles is a matter of common experience, it seems appropriate to look at some of the difficulties involved in the supersonic tunnel testing of models of such machines.

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