Abstract
Numerical investigations of the Jaxa high-lift configuration Standard Model from the 3rd AIAA CFD High Lift Prediction Workshop are performed with the in-house solver MFlow. The solver is based on a cell-centered, finite-volume method and is capable of handling various element types. Hybrid grids provided by the committee are used in the simulations. The performance of massively parallel computing and force/moment predictions are the two emphases of this chapter. The speedup rate of parallel computations is satisfactory, only deviating obviously from the theoretical rate for computations on 3,200 or more processors. The efficiency of parallel computations remains greater than 75%, even for computation on 6,400 processors. The force and moment prediction is then analyzed in detail. The initialization of the flow field plays an important role in the predictions of high-lift configurations. The simulation initiated with a converged flow field obtained at a lower angle of attack achieves better agreement with experiment compared with predictions initiated with freestream values, in terms of a larger maximum-lift coefficient. The drag-and-pitching-moment prediction is also improved. The solver shows good agreement with experiment at lower angles of attack, but more attention is needed at angles of attack near and beyond stall.
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Notes
- 1.
Data available online at https://hiliftpw.larc.nasa.gov/Workshop3/testcases.html.
- 2.
Mesh available online at ftp://hiliftpw-ftp.larc.nasa.gov/outgoing/HiLiftPW3/JSM_Grids/Committee_Grids/E-JSM_UnstrMixed_ANSA.
- 3.
The formulation can be found on https://turbmodels.larc.nasa.gov/spalart.html.
- 4.
Presentations are available at https://hiliftpw.larc.nasa.gov/Workshop3/presentations.html.
Abbreviations
- \(\alpha \) :
-
= angle of attack
- \(c_{ref }\) :
-
= mean aerodynamic chord
- Ma :
-
= Mach number
- \(Re_{c}\) :
-
= Reynolds number based on \(c_{ref}\)
- \(T_{\infty }\) :
-
= free stream temperature
- \(P_{\infty }\) :
-
= free stream static pressure
- \(\eta \) :
-
= fraction of wing span
- \(C_{L }\) :
-
= lift coefficient
- \(C_{{L}\_{max}}\) :
-
= maximum value of lift coefficient
- \(C_{D }\) :
-
= drag coefficient
- \(C_{M }\) :
-
= pitching-moment coefficient
- \(C_{p }\) :
-
= pressure coefficient
- \(C_{f }\) :
-
= skin-friction coefficient
- \(C_{fx }\) :
-
= streamwise component of skin-friction coefficient
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Chen, J., Zhang, J., Tang, J., Zhang, Y. (2018). Numerical Investigations of the Jaxa High-Lift Configuration Standard Model with MFlow Solver. In: López Mejia, O., Escobar Gomez, J. (eds) Numerical Simulation of the Aerodynamics of High-Lift Configurations. Springer, Cham. https://doi.org/10.1007/978-3-319-62136-4_4
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