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FAPeda VALIDATION 1:
Supersonic Test Case: NASA Tandem Missile Geometry from “RTO Applied Vehicle Technology Panel (AVT) TG-082” [1]


Figure 1. NASA Tandem Missile Geometry [1]


TABLE 1. Comparison of CFD Results with experimental data at  M=1.75,  Alpha=6 deg.

Authors Organization Solver (Tur.mod.) Alpha CA CN Cm CA_err CN_err cm_err

NASA (USA) exp 5.946 0.5594 1.9856 0.8521 0 0 0
Khalid NRC (CA) WIND (SA) 6 0.4930 1.9900 0.9730 -0.0664 0.0044 -0.1209
Henig LFK (GE) FASTRAN (k-e) 5.9 0.7310 2.1020 0.8190 0.1716 0.1164 0.0331
Prince QinetiQ (UK) FLUENT (SA) 6 0.4706 2.0320 0.8370 -0.0888 0.0464 0.0151
Leavitt NASA (USA) USM3Dns (SA) 6 0.7365 2.0700 0.8200 0.1771 0.0844 0.0321
Dujardin DLR (GE) TAU (SA) 6 0.6845 2.0310 0.9230 0.1251 0.0454 -0.0709
Dujardin DLR (GE) TAU (k-w) 6 0.6104 2.0090 0.8470 0.051 0.0234 0.0051
Oktay EDA (TR) FAPeda (SA) 6 0.5974 2.0860 0.8070 0.038 0.1004 0.0451


Figure 2. Differences Between Measured and Predicted Axial Force Coefficient CA for different solvers


Figure 3. Differences Between Measured and Predicted Normal Force Coefficient CN for different solvers


Figure 4. Differences Between Measured and Predicted Pitch Moment Coefficient Cm for different solvers



References:

  1. RTO Applied Vehicle Technology Panel (AVT) TG-082, “Assessment of Turbulence Modeling for High-Speed Vehicles”, TR-AVT-082, 2005.