Boundary Layer Method for Unsteady Transonic Flow

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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/article/boundary-layer-method-for-unsteady-transonic-flow/>. Date accessed: 15 sep. 2019. 
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/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/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.  15 Sep. 2019
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/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/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/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)

Authors

Affiliations

  • University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Croatia
  • Institute for Aeroelasticity, German Aerospace Center, Germany
  • University of Zagreb, Faculty of Mechanical Engineering and Naval Architecture, Croatia

Paper's information

Strojniški vestnik - Journal of Mechanical Engineering 58(2012)7-8, 470-481

10.5545/sv-jme.2011.170

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.

unsteady transonic flow; viscous-inviscid coupling; airfoil; transpiration velocity; transition prediction