scholarly journals Numerical Investigation of Supersonic Nozzle Flow Separation

AIAA Journal ◽  
2007 ◽  
Vol 45 (3) ◽  
pp. 532-541 ◽  
Author(s):  
Q. Xiao ◽  
H. M. Tsai ◽  
D. Papamoschou
Keyword(s):  
Numerical Investigation ◽  
Flow Separation ◽  
Supersonic Nozzle ◽  
Nozzle Flow

Numerical Investigation of Film Cooling Effectiveness Including Shockwave Interaction in a Supersonic Nozzle Flow

2022 ◽  
Author(s):  
Manoj Prabakar Sargunaraj ◽  
Andres Torres ◽  
Jose Garduna ◽  
Marcel Otto ◽  
Jayanta S. Kapat ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Film Cooling ◽  
Supersonic Nozzle ◽  
Nozzle Flow ◽  
Cooling Effectiveness ◽  
Film Cooling Effectiveness

Experimental and numerical investigation of flow separation in a supersonic nozzle

2008 ◽  
Vol 29 (4) ◽  
pp. 377-389 ◽  
Author(s):  
Slavica Ristić ◽  
Mirko Kozić ◽  
Mirjana Puharić
Keyword(s):  
Numerical Investigation ◽  
Flow Separation ◽  
Supersonic Nozzle

Nozzle flow separation

AIAA Journal ◽  
1998 ◽  
Vol 36 ◽  
pp. 1618-1625 ◽  
Author(s):  
G. L. Romine
Keyword(s):  
Flow Separation ◽  
Nozzle Flow

Numerical Investigation of Cowl Lip Adjustments for a Rocket-Based Combined-Cycle Inlet in Takeoff Regime

2016 ◽  
Vol 33 (3) ◽  
Author(s):  
Lei Shi ◽  
Xiaowei Liu ◽  
Guoqiang He ◽  
Fei Qin ◽  
Xianggeng Wei ◽  
...  
Keyword(s):  
Numerical Integration ◽  
Numerical Investigation ◽  
Flow Separation ◽  
Static Condition ◽  
Combined Cycle ◽  
Variable Geometry ◽  
Overall Performance ◽  
Negative Impacts

AbstractNumerical integration simulations were performed on a ready-made central strut-based rocket-based combined-cycle (RBCC) engine operating in the ejector mode during the takeoff regime. The effective principles of various cowl lip positions and shapes on the inlet operation and the overall performance of the entire engine were investigated in detail. Under the static condition, reverse cowl lip rotation in a certain range was found to contribute comprehensive improvement to the RBCC inlet and the entire engine. However, the reverse rotation of the cowl lip contributed very little enhancement of the RBCC inlet under the low subsonic flight regime and induced extremely negative impacts in the high subsonic flight regime, especially in terms of a significant increase in the drag of the inlet. Changes to the cowl lip shape provided little improvement to the overall performance of the RBCC engine, merely shifting the location of the leeward area inside the RBCC inlet, as well as the flow separation and eddy, but not relieving or eliminating those phenomena. The results of this study indicate that proper cowl lip rotation offers an efficient variable geometry scheme for a RBCC inlet in the takeoff regime.

Experimental and numerical investigation of heat loads in separated nozzle flow

2001 ◽  
Author(s):  
A. Gross ◽  
O. Haidn ◽  
R. Stark ◽  
W. Zeiss ◽  
C. Weber ◽  
...  
Keyword(s):  
Numerical Investigation ◽  
Nozzle Flow ◽  
Heat Loads
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