MAJIĆ, Frane ;VOSS, Ralph ;VIRAG, Zdravko . Boundary Layer Method for Unsteady Transonic Flow. Strojniški vestnik - Journal of Mechanical Engineering, [S.l.], v. 58, n.7-8, p. 470-481, june 2018. ISSN 0039-2480. Available at: <https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/>. Date accessed: 19 nov. 2024. doi:http://dx.doi.org/10.5545/sv-jme.2011.170.
Majić, F., Voss, R., & Virag, Z. (2012). Boundary Layer Method for Unsteady Transonic Flow. Strojniški vestnik - Journal of Mechanical Engineering, 58(7-8), 470-481. doi:http://dx.doi.org/10.5545/sv-jme.2011.170
@article{sv-jmesv-jme.2011.170,
author = {Frane Majić and Ralph Voss and Zdravko Virag},
title = {Boundary Layer Method for Unsteady Transonic Flow},
journal = {Strojniški vestnik - Journal of Mechanical Engineering},
volume = {58},
number = {7-8},
year = {2012},
keywords = {unsteady transonic flow; viscous-inviscid coupling; airfoil; transpiration velocity; transition prediction},
abstract = {A numerical method for determination of unsteady loads in a 2-D transonic flow, with the occurrence of a shock wave, on a pitching airfoil is demonstrated. The method implements the Euler equations for inviscid region and integral boundary layer equations for the viscous region near the airfoil. The viscous-inviscid interaction method is employed using the transpiration velocity concept on the airfoil contour. The Euler solution is calculated by using the Van Leer flux-vector splitting method on the body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for the laminar and turbulent flow. The transition from the laminar to the turbulent flow is predicted by the en method. The viscous-inviscid interaction method is made in the direct mode. The results obtained by this method are comparable with the calculated RANS and experimental results, while time and computational costs were lower than for RANS calculations. Generally, the pressure coefficient distribution results showed good agreement with the RANS and experimental results. The method predicted the position of a shock wave to be slightly shifted towards the leading edge of the airfoil with respect to the position obtained by the RANS and experimental results. This indicates that the boundary layer model has a strong influence on the inviscid part of the flow.},
issn = {0039-2480}, pages = {470-481}, doi = {10.5545/sv-jme.2011.170},
url = {https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/}
}
Majić, F.,Voss, R.,Virag, Z. 2012 June 58. Boundary Layer Method for Unsteady Transonic Flow. Strojniški vestnik - Journal of Mechanical Engineering. [Online] 58:7-8
%A Majić, Frane %A Voss, Ralph %A Virag, Zdravko %D 2012 %T Boundary Layer Method for Unsteady Transonic Flow %B 2012 %9 unsteady transonic flow; viscous-inviscid coupling; airfoil; transpiration velocity; transition prediction %! Boundary Layer Method for Unsteady Transonic Flow %K unsteady transonic flow; viscous-inviscid coupling; airfoil; transpiration velocity; transition prediction %X A numerical method for determination of unsteady loads in a 2-D transonic flow, with the occurrence of a shock wave, on a pitching airfoil is demonstrated. The method implements the Euler equations for inviscid region and integral boundary layer equations for the viscous region near the airfoil. The viscous-inviscid interaction method is employed using the transpiration velocity concept on the airfoil contour. The Euler solution is calculated by using the Van Leer flux-vector splitting method on the body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for the laminar and turbulent flow. The transition from the laminar to the turbulent flow is predicted by the en method. The viscous-inviscid interaction method is made in the direct mode. The results obtained by this method are comparable with the calculated RANS and experimental results, while time and computational costs were lower than for RANS calculations. Generally, the pressure coefficient distribution results showed good agreement with the RANS and experimental results. The method predicted the position of a shock wave to be slightly shifted towards the leading edge of the airfoil with respect to the position obtained by the RANS and experimental results. This indicates that the boundary layer model has a strong influence on the inviscid part of the flow. %U https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/ %0 Journal Article %R 10.5545/sv-jme.2011.170 %& 470 %P 12 %J Strojniški vestnik - Journal of Mechanical Engineering %V 58 %N 7-8 %@ 0039-2480 %8 2018-06-28 %7 2018-06-28
Majić, Frane, Ralph Voss, & Zdravko Virag. "Boundary Layer Method for Unsteady Transonic Flow." Strojniški vestnik - Journal of Mechanical Engineering [Online], 58.7-8 (2012): 470-481. Web. 19 Nov. 2024
TY - JOUR AU - Majić, Frane AU - Voss, Ralph AU - Virag, Zdravko PY - 2012 TI - Boundary Layer Method for Unsteady Transonic Flow JF - Strojniški vestnik - Journal of Mechanical Engineering DO - 10.5545/sv-jme.2011.170 KW - unsteady transonic flow; viscous-inviscid coupling; airfoil; transpiration velocity; transition prediction N2 - A numerical method for determination of unsteady loads in a 2-D transonic flow, with the occurrence of a shock wave, on a pitching airfoil is demonstrated. The method implements the Euler equations for inviscid region and integral boundary layer equations for the viscous region near the airfoil. The viscous-inviscid interaction method is employed using the transpiration velocity concept on the airfoil contour. The Euler solution is calculated by using the Van Leer flux-vector splitting method on the body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for the laminar and turbulent flow. The transition from the laminar to the turbulent flow is predicted by the en method. The viscous-inviscid interaction method is made in the direct mode. The results obtained by this method are comparable with the calculated RANS and experimental results, while time and computational costs were lower than for RANS calculations. Generally, the pressure coefficient distribution results showed good agreement with the RANS and experimental results. The method predicted the position of a shock wave to be slightly shifted towards the leading edge of the airfoil with respect to the position obtained by the RANS and experimental results. This indicates that the boundary layer model has a strong influence on the inviscid part of the flow. UR - https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/
@article{{sv-jme}{sv-jme.2011.170},
author = {Majić, F., Voss, R., Virag, Z.},
title = {Boundary Layer Method for Unsteady Transonic Flow},
journal = {Strojniški vestnik - Journal of Mechanical Engineering},
volume = {58},
number = {7-8},
year = {2012},
doi = {10.5545/sv-jme.2011.170},
url = {https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/}
}
TY - JOUR AU - Majić, Frane AU - Voss, Ralph AU - Virag, Zdravko PY - 2018/06/28 TI - Boundary Layer Method for Unsteady Transonic Flow JF - Strojniški vestnik - Journal of Mechanical Engineering; Vol 58, No 7-8 (2012): Strojniški vestnik - Journal of Mechanical Engineering DO - 10.5545/sv-jme.2011.170 KW - unsteady transonic flow, viscous-inviscid coupling, airfoil, transpiration velocity, transition prediction N2 - A numerical method for determination of unsteady loads in a 2-D transonic flow, with the occurrence of a shock wave, on a pitching airfoil is demonstrated. The method implements the Euler equations for inviscid region and integral boundary layer equations for the viscous region near the airfoil. The viscous-inviscid interaction method is employed using the transpiration velocity concept on the airfoil contour. The Euler solution is calculated by using the Van Leer flux-vector splitting method on the body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for the laminar and turbulent flow. The transition from the laminar to the turbulent flow is predicted by the en method. The viscous-inviscid interaction method is made in the direct mode. The results obtained by this method are comparable with the calculated RANS and experimental results, while time and computational costs were lower than for RANS calculations. Generally, the pressure coefficient distribution results showed good agreement with the RANS and experimental results. The method predicted the position of a shock wave to be slightly shifted towards the leading edge of the airfoil with respect to the position obtained by the RANS and experimental results. This indicates that the boundary layer model has a strong influence on the inviscid part of the flow. UR - https://www.sv-jme.eu/sl/article/boundary-layer-method-for-unsteady-transonic-flow/
Majić, Frane, Voss, Ralph, AND Virag, Zdravko. "Boundary Layer Method for Unsteady Transonic Flow" Strojniški vestnik - Journal of Mechanical Engineering [Online], Volume 58 Number 7-8 (28 June 2018)
Strojniški vestnik - Journal of Mechanical Engineering 58(2012)7-8, 470-481
© The Authors, CC-BY 4.0 Int. Change in copyright policy from 2022, Jan 1st.
A numerical method for determination of unsteady loads in a 2-D transonic flow, with the occurrence of a shock wave, on a pitching airfoil is demonstrated. The method implements the Euler equations for inviscid region and integral boundary layer equations for the viscous region near the airfoil. The viscous-inviscid interaction method is employed using the transpiration velocity concept on the airfoil contour. The Euler solution is calculated by using the Van Leer flux-vector splitting method on the body-fitted C-grid. The boundary layer model is calculated applying Drela’s model of integral boundary layer equations for the laminar and turbulent flow. The transition from the laminar to the turbulent flow is predicted by the en method. The viscous-inviscid interaction method is made in the direct mode. The results obtained by this method are comparable with the calculated RANS and experimental results, while time and computational costs were lower than for RANS calculations. Generally, the pressure coefficient distribution results showed good agreement with the RANS and experimental results. The method predicted the position of a shock wave to be slightly shifted towards the leading edge of the airfoil with respect to the position obtained by the RANS and experimental results. This indicates that the boundary layer model has a strong influence on the inviscid part of the flow.