Abstract
An analysis is presented to simulate the highly turbulent compressible flow in truncated diverging nozzle used for reverse thrust and in stage separations for aerospace applications. Flow simulation is done by solving thin layer Navier-Stroke (TLNS) equations and using McCormack time-marching finite difference scheme. Using an algebraic two-layer eddy viscosity, model proposed by Baldwin-Lomax incorporates the effects of turbulence. The presence of a supersonic step near the throat causes the formation of characteristics twin peaks in the flow regime. Thus, advocating the presence of high turbulent flow field with shocks. Further, to this, shock waves appear in series and flow separation exists in the flow field of the truncated nozzle. The flow field simulation also shows various regions of re-circulating flow and lip re-attachment clockwise zones near the wall. Contour plots clearly show the separation points, re- circulation zone and re-attachment points in the flow along the nozzle wall. The present study in addition to flow field calculation can further be used to stimulate the side loads acting on nozzle walls. Also, the resulting temperatures can be used to design the thermal protection system for such types of truncated nozzle desirable to operate efficiently for short duration. The results obtained
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Citation Formats
Raza, M A, and Chaudhry, S R.
Numerical Flow Simulation of Formation of Turbulent Twin Peaks in Truncated Diverging Nozzle.
Pakistan: N. p.,
2004.
Web.
Raza, M A, & Chaudhry, S R.
Numerical Flow Simulation of Formation of Turbulent Twin Peaks in Truncated Diverging Nozzle.
Pakistan.
Raza, M A, and Chaudhry, S R.
2004.
"Numerical Flow Simulation of Formation of Turbulent Twin Peaks in Truncated Diverging Nozzle."
Pakistan.
@misc{etde_20618807,
title = {Numerical Flow Simulation of Formation of Turbulent Twin Peaks in Truncated Diverging Nozzle}
author = {Raza, M A, and Chaudhry, S R}
abstractNote = {An analysis is presented to simulate the highly turbulent compressible flow in truncated diverging nozzle used for reverse thrust and in stage separations for aerospace applications. Flow simulation is done by solving thin layer Navier-Stroke (TLNS) equations and using McCormack time-marching finite difference scheme. Using an algebraic two-layer eddy viscosity, model proposed by Baldwin-Lomax incorporates the effects of turbulence. The presence of a supersonic step near the throat causes the formation of characteristics twin peaks in the flow regime. Thus, advocating the presence of high turbulent flow field with shocks. Further, to this, shock waves appear in series and flow separation exists in the flow field of the truncated nozzle. The flow field simulation also shows various regions of re-circulating flow and lip re-attachment clockwise zones near the wall. Contour plots clearly show the separation points, re- circulation zone and re-attachment points in the flow along the nozzle wall. The present study in addition to flow field calculation can further be used to stimulate the side loads acting on nozzle walls. Also, the resulting temperatures can be used to design the thermal protection system for such types of truncated nozzle desirable to operate efficiently for short duration. The results obtained are in good agreement with the results presented in the literature by Chen and Hou and Dumnov, Hagmann and Koschel. (author)}
place = {Pakistan}
year = {2004}
month = {Jul}
}
title = {Numerical Flow Simulation of Formation of Turbulent Twin Peaks in Truncated Diverging Nozzle}
author = {Raza, M A, and Chaudhry, S R}
abstractNote = {An analysis is presented to simulate the highly turbulent compressible flow in truncated diverging nozzle used for reverse thrust and in stage separations for aerospace applications. Flow simulation is done by solving thin layer Navier-Stroke (TLNS) equations and using McCormack time-marching finite difference scheme. Using an algebraic two-layer eddy viscosity, model proposed by Baldwin-Lomax incorporates the effects of turbulence. The presence of a supersonic step near the throat causes the formation of characteristics twin peaks in the flow regime. Thus, advocating the presence of high turbulent flow field with shocks. Further, to this, shock waves appear in series and flow separation exists in the flow field of the truncated nozzle. The flow field simulation also shows various regions of re-circulating flow and lip re-attachment clockwise zones near the wall. Contour plots clearly show the separation points, re- circulation zone and re-attachment points in the flow along the nozzle wall. The present study in addition to flow field calculation can further be used to stimulate the side loads acting on nozzle walls. Also, the resulting temperatures can be used to design the thermal protection system for such types of truncated nozzle desirable to operate efficiently for short duration. The results obtained are in good agreement with the results presented in the literature by Chen and Hou and Dumnov, Hagmann and Koschel. (author)}
place = {Pakistan}
year = {2004}
month = {Jul}
}