Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear

386 Views
149 Downloads
Export citation: ABNT
OZALP, A. Alper .
Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear. 
Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 53, n.1, p. 3-12, august 2017. 
ISSN 0039-2480.
Available at: <https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/>. Date accessed: 15 sep. 2019. 
doi:http://dx.doi.org/.
Ozalp, A.
(2007).
Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear.
Strojniški vestnik - Journal of Mechanical Engineering, 53(1), 3-12.
doi:http://dx.doi.org/
@article{.,
	author = {A. Alper  Ozalp},
	title = {Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {53},
	number = {1},
	year = {2007},
	keywords = {propulsion nozzle; compressible flow; discharge coefficient; power losses; },
	abstract = {Numerical simulations of aerospace propulsion nozzles are very complex due to the necessity to simultaneously handle flow acceleration, momentum heat-transfer rates, surface roughness, temperaturedependent air properties and streamwise density variations due to the compressible character of the flow. To provide an overview for a multitask consideration of the propulsion-nozzle flows, a new computational model that integrates the axi-symmetrical continuity, the momentum and the energy equations has been developed. Numerical experiments were performed with various nozzle geometries, inlet-boundary conditions, with the combined handling of the surface heat flux and roughness conditions. The computations indicated that the input and loss power values of the propulsion nozzle increase with higher inlet stagnation pressures and decrease with higher nozzle convergence half angles and surface heat flux. The ratio of the loss to the input power was found to be independent of the heat flux; however, it decreases linearly with an increase in the convergence half angles.},
	issn = {0039-2480},	pages = {3-12},	doi = {},
	url = {https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/}
}
Ozalp, A.
2007 August 53. Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 53:1
%A Ozalp, A. Alper 
%D 2007
%T Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear
%B 2007
%9 propulsion nozzle; compressible flow; discharge coefficient; power losses; 
%! Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear
%K propulsion nozzle; compressible flow; discharge coefficient; power losses; 
%X Numerical simulations of aerospace propulsion nozzles are very complex due to the necessity to simultaneously handle flow acceleration, momentum heat-transfer rates, surface roughness, temperaturedependent air properties and streamwise density variations due to the compressible character of the flow. To provide an overview for a multitask consideration of the propulsion-nozzle flows, a new computational model that integrates the axi-symmetrical continuity, the momentum and the energy equations has been developed. Numerical experiments were performed with various nozzle geometries, inlet-boundary conditions, with the combined handling of the surface heat flux and roughness conditions. The computations indicated that the input and loss power values of the propulsion nozzle increase with higher inlet stagnation pressures and decrease with higher nozzle convergence half angles and surface heat flux. The ratio of the loss to the input power was found to be independent of the heat flux; however, it decreases linearly with an increase in the convergence half angles.
%U https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/
%0 Journal Article
%R 
%& 3
%P 10
%J Strojniški vestnik - Journal of Mechanical Engineering
%V 53
%N 1
%@ 0039-2480
%8 2017-08-18
%7 2017-08-18
Ozalp, A. Alper.
"Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear." Strojniški vestnik - Journal of Mechanical Engineering [Online], 53.1 (2007): 3-12. Web.  15 Sep. 2019
TY  - JOUR
AU  - Ozalp, A. Alper 
PY  - 2007
TI  - Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear
JF  - Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - propulsion nozzle; compressible flow; discharge coefficient; power losses; 
N2  - Numerical simulations of aerospace propulsion nozzles are very complex due to the necessity to simultaneously handle flow acceleration, momentum heat-transfer rates, surface roughness, temperaturedependent air properties and streamwise density variations due to the compressible character of the flow. To provide an overview for a multitask consideration of the propulsion-nozzle flows, a new computational model that integrates the axi-symmetrical continuity, the momentum and the energy equations has been developed. Numerical experiments were performed with various nozzle geometries, inlet-boundary conditions, with the combined handling of the surface heat flux and roughness conditions. The computations indicated that the input and loss power values of the propulsion nozzle increase with higher inlet stagnation pressures and decrease with higher nozzle convergence half angles and surface heat flux. The ratio of the loss to the input power was found to be independent of the heat flux; however, it decreases linearly with an increase in the convergence half angles.
UR  - https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/
@article{{}{.},
	author = {Ozalp, A.},
	title = {Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear},
	journal = {Strojniški vestnik - Journal of Mechanical Engineering},
	volume = {53},
	number = {1},
	year = {2007},
	doi = {},
	url = {https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/}
}
TY  - JOUR
AU  - Ozalp, A. Alper 
PY  - 2017/08/18
TI  - Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear
JF  - Strojniški vestnik - Journal of Mechanical Engineering; Vol 53, No 1 (2007): Strojniški vestnik - Journal of Mechanical Engineering
DO  - 
KW  - propulsion nozzle, compressible flow, discharge coefficient, power losses, 
N2  - Numerical simulations of aerospace propulsion nozzles are very complex due to the necessity to simultaneously handle flow acceleration, momentum heat-transfer rates, surface roughness, temperaturedependent air properties and streamwise density variations due to the compressible character of the flow. To provide an overview for a multitask consideration of the propulsion-nozzle flows, a new computational model that integrates the axi-symmetrical continuity, the momentum and the energy equations has been developed. Numerical experiments were performed with various nozzle geometries, inlet-boundary conditions, with the combined handling of the surface heat flux and roughness conditions. The computations indicated that the input and loss power values of the propulsion nozzle increase with higher inlet stagnation pressures and decrease with higher nozzle convergence half angles and surface heat flux. The ratio of the loss to the input power was found to be independent of the heat flux; however, it decreases linearly with an increase in the convergence half angles.
UR  - https://www.sv-jme.eu/article/parallel-effects-of-acceleration-and-surface-heating-on-compressible-flow-simulation-of-an-aerospace-propulsion-nozzle-with-a-medium-amount-of-surface-wear/
Ozalp, A. Alper"Parallel Effects of Acceleration and Surface Heating on Compressible Flow: Simulation of an Aerospace Propulsion Nozzle with a Medium Amount of Surface Wear" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 53 Number 1 (18 August 2017)

Authors

Affiliations

  • Uludag University, Turkey

Paper's information

Strojniški vestnik - Journal of Mechanical Engineering 53(2007)1, 3-12

Numerical simulations of aerospace propulsion nozzles are very complex due to the necessity to simultaneously handle flow acceleration, momentum heat-transfer rates, surface roughness, temperaturedependent air properties and streamwise density variations due to the compressible character of the flow. To provide an overview for a multitask consideration of the propulsion-nozzle flows, a new computational model that integrates the axi-symmetrical continuity, the momentum and the energy equations has been developed. Numerical experiments were performed with various nozzle geometries, inlet-boundary conditions, with the combined handling of the surface heat flux and roughness conditions. The computations indicated that the input and loss power values of the propulsion nozzle increase with higher inlet stagnation pressures and decrease with higher nozzle convergence half angles and surface heat flux. The ratio of the loss to the input power was found to be independent of the heat flux; however, it decreases linearly with an increase in the convergence half angles.

propulsion nozzle; compressible flow; discharge coefficient; power losses;