Unsteady Phenomena in Supersonic Nozzle Flow Separation

2006 ◽  
Author(s):  
Dimitri Papamoschou ◽  
Andrew Johnson
Keyword(s):  
Flow Separation ◽  
Supersonic Nozzle ◽  
Nozzle Flow

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

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 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

Experiments on water vapour condensation within supersonic nozzle flow generated by an impulse tunnel

2021 ◽  
Vol 134 ◽  
pp. 103473
Author(s):  
Jafar Mahmoudian ◽  
Federico Mazzelli ◽  
Adriano Milazzo ◽  
Ray Malpress ◽  
David R. Buttsworth
Keyword(s):  
Water Vapour ◽  
Supersonic Nozzle ◽  
Nozzle Flow ◽  
Vapour Condensation

scholarly journals Computational and Experimental Study of Supersonic Nozzle Flow and Aft-Deck Interactions

2016 ◽  
Author(s):  
Walter E. Bruce ◽  
Melissa B. Carter ◽  
Alaa A. Elmiligui ◽  
Courtney S. Winski ◽  
Sudheer Nayani ◽  
...  
Keyword(s):  
Experimental Study ◽  
Supersonic Nozzle ◽  
Nozzle Flow

scholarly journals Numerical Simulation of Reactive Flows in Overexpanded Supersonic Nozzle with Film Cooling

2015 ◽  
Vol 2015 ◽  
pp. 1-15 ◽  
Author(s):  
Mohamed Sellam ◽  
Amer Chpoun
Keyword(s):  
Film Cooling ◽  
Structural Integrity ◽  
Safety Issue ◽  
Rocket Engine ◽  
Supersonic Nozzle ◽  
Nozzle Geometry ◽  
Nozzle Flow ◽  
Rocket Engines ◽  
Flow Conditions ◽  
Reactive Flows

Reignition phenomena occurring in a supersonic nozzle flow may present a crucial safety issue for rocket propulsion systems. These phenomena concern mainly rocket engines which use H2gas (GH2) in the film cooling device, particularly when the nozzle operates under over expanded flow conditions at sea level or at low altitudes. Consequently, the induced wall thermal loads can lead to the nozzle geometry alteration, which in turn, leads to the appearance of strong side loads that may be detrimental to the rocket engine structural integrity. It is therefore necessary to understand both aerodynamic and chemical mechanisms that are at the origin of these processes. This paper is a numerical contribution which reports results from CFD analysis carried out for supersonic reactive flows in a planar nozzle cooled with GH2film. Like the experimental observations, CFD simulations showed their ability to highlight these phenomena for the same nozzle flow conditions. Induced thermal load are also analyzed in terms of cooling efficiency and the results already give an idea on their magnitude. It was also shown that slightly increasing the film injection pressure can avoid the reignition phenomena by moving the separation shock towards the nozzle exit section.

Development of a Freejet Capability for Evaluating Inlet-Engine Compatibility

1991 ◽  
Author(s):  
P. V. Maywald ◽  
D. K. Beale
Keyword(s):  
Technology Development ◽  
Support Systems ◽  
Supersonic Nozzle ◽  
Test Facility ◽  
Nozzle Flow ◽  
Propulsion Systems ◽  
Turbine Engine ◽  
Development Center ◽  
Subsonic Nozzle

The Arnold Engineering Development Center (AEDC) is installing a freejet test capability into the Aero-propulsion Systems Test Facility (ASTF). The freejet will provide the capability for ground determination of turbine engine and aircraft inlet compatibility by utilizing full-scale inlets and engines as test articles in a simulated flight environment. The details of the design, installation, and projected testing capability are described for a 57 ft2 supersonic nozzle and a 77 ft2 subsonic nozzle. Support systems for mechanically pitching and yawing the freejet nozzles are also reported as well as the test cell hardware for capturing the freejet nozzle flow. The plans for demonstrating the freejet capability prior to its initial operational date are explained. The technology development efforts to validate and utilize the freejet test capabilities are also described.

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