scholarly journals Experiment of two-dimensional supersonic nozzle flow using visualization of flow.

1989 ◽  
Vol 9 (35) ◽  
pp. 430-434
Author(s):  
Shigeru YAMANAKA
Keyword(s):  
Supersonic Nozzle ◽  
Nozzle Flow ◽  
Two Dimensional

Chemical Nonequilibrium in Supersonic Nozzle Flow

1971 ◽  
Vol 93 (4) ◽  
pp. 576-586
Author(s):  
Roa-Ling Wang
Keyword(s):  
Static Pressure ◽  
Theoretical Study ◽  
Supersonic Nozzle ◽  
Reactive System ◽  
Nozzle Flow ◽  
Two Dimensional ◽  
Chemical Nonequilibrium ◽  
One Dimensional ◽  
Nonequilibrium Flows ◽  
Good Agreement

An experimental and theoretical study has been made on chemical nonequilibrium flows in a supersonic nozzle for a mixture of dissociated gases and inert diluent. In the calculations, four different flow behaviors were assumed: one-dimensional non-equilibrium, two-dimensional nonequilibrium, two-dimensional equilibrium, and two-dimensional frozen flows. These were compared with measurements of the static pressure and NO2 concentration in the supersonic nozzle flow of the NO2-N4O2-N2 reactive system. Relatively good agreement demonstrates the applicability of the proposed calculation methods and the validity of the assumed reaction mechanisms and their rate constants.

Two-dimensional multispecies imaging of a supersonic nozzle flow

1999 ◽  
Vol 24 (10) ◽  
pp. 664 ◽  
Author(s):  
N. M. Sijtsema ◽  
R. A. L. Tolboom ◽  
N. J. Dam ◽  
J. J. ter Meulen
Keyword(s):  
Supersonic Nozzle ◽  
Nozzle Flow ◽  
Two Dimensional

Analysis of the Impact of Specific Heat Ratio on Two-Dimensional Low Maher Number Nozzle Design

2014 ◽  
Vol 590 ◽  
pp. 546-550
Author(s):  
Zhi Qiang Fan ◽  
Hai Bo Yang ◽  
Fei Zhao ◽  
Rong Zhu ◽  
Dong Bai Sun
Keyword(s):  
Specific Heat ◽  
Supersonic Nozzle ◽  
Two Dimensional ◽  
Nozzle Design ◽  
Scheme Design ◽  
Specific Heat Ratio ◽  
Nozzle Contour ◽  
Ratio Change ◽  
Change Impact ◽  
The Impact

The practical requirements of the project the nozzle entrance temperature is high, the gas specific heat ratio varies greatly, so it must consider the specific heat ratio change impact on two-dimensional nozzle contour design. Divided into consideration specific heat ratio change and not consider two kinds of scheme design of 1.4Ma nozzle profile and build the model using the arc line method, numerical simulation is carried out through the CFD software Fluent, analysis of two kinds of design scheme comparison. The results show that, in the supersonic nozzle at low Maher numbers, two schemes of nozzle design profile similarity, parameters change little flow tube, export the Maher number and the flow quality can meet the design requirements, proof of specific heat ratio has little effect on the design results in the design of the nozzle under the condition of low Maher number.

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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