Locating the Isolator Shock-Train Leading Edge with Limited Pressure Information

2021 ◽  
pp. 1-17
Author(s):  
Gregory J. Hunt ◽  
Robin L. Hunt
Keyword(s):  
Author(s):  
B Xiong ◽  
Z-G Wang ◽  
X-Q Fan ◽  
Y Wang

In order to make the shock train leading edge detection method more possible for operational application, a new detection method based on differential pressure signals is introduced in this paper. Firstly, three previous detection methods, including the pressure ratio method, the pressure increase method, and the standard deviation method, have been examined whether they are also applicable for shock train moving at different speeds. Accordingly, three experimental cases of back-pressure changing at different rates were conducted in this paper. The results show that the pressure ratio and the pressure increase method both have acceptable detection accuracy for shock train moving rapidly and slowly, and the standard deviation method is not applicable for rapid shock train movement due to its running time window. Considering the operational application, the differential pressure method is raised and tested in this paper. This detection method has sufficient temporal resolution for rapidly and slowly shock train moving, and can make a real-time detection. In the end, the improvements brought by the differential pressure method have been discussed.


Author(s):  
Santhosh Kumar Gugulothu ◽  
B. Bhaskar ◽  
V.V. Phani Babu

Numerical simulations are carried out to study the effect of divergence angle and adverse pressure gradient on the movement of shock wave train in a scramjet isolator. The commercial software tool ANSYS Fluent 16 was used to simplify two dimensional Reynolds averaged Navier Stokes equation with compressible fluid flow by considering the density-based solver with standard K-ε turbulence model. The species transport model with single step volumetric reaction mechanism is employed. Initially, the simulated results are validated with experimental results available in open literature. The obtained results show that the variation of the divergence angle and back pressure on the scramjet isolator has greater significance on the flow field. Also, with an increase in the back pressure, due to the intense turbulent combustion, the shock wave train developed should expand along the length and also moves towards the leading edge of the isolator leading to rapid rise in the pressure so that the pressure at the entrance of the isolator can match the enhanced back pressures.


Author(s):  
Daniel Le ◽  
Christopher Goyne ◽  
Roland Krauss ◽  
James McDaniel

2008 ◽  
Vol 24 (5) ◽  
pp. 1035-1041 ◽  
Author(s):  
D. B. Le ◽  
C. P. Goyne ◽  
R. H. Krauss

AIAA Journal ◽  
2020 ◽  
Vol 58 (9) ◽  
pp. 4068-4080 ◽  
Author(s):  
Chen Kong ◽  
Juntao Chang ◽  
Yunfei Li ◽  
Nan Li

2015 ◽  
Vol 28 (2) ◽  
pp. 04014064 ◽  
Author(s):  
Jichao Hu ◽  
Juntao Chang ◽  
Bin Qin ◽  
Lei Wang ◽  
Wen Bao ◽  
...  

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