NASA SC(2)-0012 AIRFOIL (sc20012-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0012 AIRFOIL (sc20012-il) Reynolds number: 200,000 Max Cl/Cd: 36 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20012-il-200000.txt Download as CSV file: xf-sc20012-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0012 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8387 0.08485 0.08066 -0.0255 1.0000 0.0476
-12.250 -0.8536 0.07875 0.07450 -0.0282 1.0000 0.0473
-12.000 -0.8746 0.07269 0.06834 -0.0307 1.0000 0.0469
-11.750 -0.8985 0.06710 0.06260 -0.0322 1.0000 0.0465
-11.500 -0.9248 0.06204 0.05735 -0.0321 1.0000 0.0461
-11.250 -0.9510 0.05760 0.05268 -0.0301 1.0000 0.0458
-11.000 -0.9731 0.05356 0.04836 -0.0268 1.0000 0.0456
-10.750 -0.9876 0.04924 0.04368 -0.0239 1.0000 0.0454
-10.500 -0.9948 0.04511 0.03915 -0.0212 1.0000 0.0454
-10.250 -0.9952 0.04142 0.03503 -0.0187 1.0000 0.0457
-10.000 -0.9900 0.03819 0.03136 -0.0164 1.0000 0.0463
-9.750 -0.9805 0.03547 0.02816 -0.0144 1.0000 0.0471
-9.500 -0.9671 0.03291 0.02522 -0.0127 1.0000 0.0482
-9.250 -0.9462 0.03123 0.02355 -0.0123 1.0000 0.0495
-9.000 -0.9249 0.03020 0.02249 -0.0116 1.0000 0.0514
-8.750 -0.9049 0.02892 0.02096 -0.0106 1.0000 0.0537
-8.500 -0.8847 0.02722 0.01900 -0.0096 1.0000 0.0560
-8.250 -0.8616 0.02605 0.01789 -0.0092 1.0000 0.0583
-8.000 -0.8389 0.02506 0.01680 -0.0085 1.0000 0.0610
-7.750 -0.8166 0.02412 0.01563 -0.0075 1.0000 0.0640
-7.500 -0.7933 0.02293 0.01457 -0.0072 1.0000 0.0674
-7.250 -0.7706 0.02226 0.01384 -0.0064 1.0000 0.0711
-7.000 -0.7482 0.02128 0.01278 -0.0056 1.0000 0.0748
-6.750 -0.7265 0.02057 0.01216 -0.0047 1.0000 0.0786
-6.500 -0.7057 0.02006 0.01159 -0.0035 1.0000 0.0827
-6.250 -0.6866 0.01921 0.01075 -0.0021 1.0000 0.0865
-6.000 -0.6703 0.01869 0.01031 -0.0003 1.0000 0.0903
-5.750 -0.6577 0.01836 0.00996 0.0023 1.0000 0.0941
-5.500 -0.6477 0.01800 0.00957 0.0051 1.0000 0.0975
-5.250 -0.6229 0.01736 0.00903 0.0049 0.9976 0.1031
-5.000 -0.5851 0.01678 0.00843 0.0025 0.9936 0.1108
-4.750 -0.5502 0.01608 0.00783 0.0005 0.9884 0.1206
-4.500 -0.5142 0.01538 0.00722 -0.0017 0.9841 0.1347
-4.250 -0.4800 0.01462 0.00665 -0.0036 0.9794 0.1592
-4.000 -0.4485 0.01362 0.00608 -0.0052 0.9741 0.2237
-3.750 -0.4196 0.01203 0.00549 -0.0068 0.9702 0.4080
-3.500 -0.3960 0.01113 0.00565 -0.0060 0.9643 0.6217
-3.250 -0.3633 0.01121 0.00581 -0.0066 0.9588 0.6868
-3.000 -0.3283 0.01130 0.00591 -0.0077 0.9550 0.7198
-2.750 -0.2982 0.01143 0.00604 -0.0078 0.9495 0.7433
-2.500 -0.2687 0.01155 0.00617 -0.0077 0.9440 0.7627
-2.250 -0.2371 0.01166 0.00627 -0.0080 0.9396 0.7794
-2.000 -0.2072 0.01179 0.00642 -0.0078 0.9352 0.7958
-1.750 -0.1823 0.01196 0.00659 -0.0067 0.9287 0.8114
-1.500 -0.1550 0.01210 0.00673 -0.0061 0.9240 0.8264
-1.250 -0.1266 0.01225 0.00691 -0.0054 0.9203 0.8385
-1.000 -0.1021 0.01241 0.00709 -0.0042 0.9144 0.8504
-0.500 -0.0505 0.01265 0.00736 -0.0022 0.9040 0.8719
-0.250 -0.0253 0.01271 0.00740 -0.0013 0.8985 0.8827
0.000 0.0000 0.01282 0.00754 0.0000 0.8906 0.8906
0.250 0.0253 0.01271 0.00740 0.0013 0.8826 0.8985
0.500 0.0505 0.01265 0.00736 0.0022 0.8719 0.9040
0.750 0.0776 0.01253 0.00720 0.0032 0.8631 0.9084
1.000 0.1021 0.01241 0.00709 0.0042 0.8505 0.9144
1.250 0.1266 0.01225 0.00691 0.0054 0.8385 0.9203
1.500 0.1550 0.01210 0.00673 0.0061 0.8264 0.9241
1.750 0.1823 0.01196 0.00659 0.0067 0.8114 0.9287
2.000 0.2071 0.01179 0.00641 0.0078 0.7958 0.9352
2.250 0.2371 0.01166 0.00627 0.0080 0.7793 0.9396
2.500 0.2687 0.01155 0.00617 0.0077 0.7626 0.9440
2.750 0.2982 0.01143 0.00604 0.0078 0.7434 0.9495
3.000 0.3283 0.01130 0.00591 0.0077 0.7198 0.9551
3.250 0.3633 0.01121 0.00581 0.0066 0.6869 0.9589
3.500 0.3960 0.01113 0.00565 0.0060 0.6220 0.9643
3.750 0.4196 0.01203 0.00548 0.0068 0.4081 0.9703
4.000 0.4485 0.01362 0.00608 0.0052 0.2236 0.9741
4.250 0.4800 0.01462 0.00665 0.0036 0.1592 0.9795
4.500 0.5142 0.01538 0.00722 0.0017 0.1347 0.9842
4.750 0.5503 0.01608 0.00782 -0.0005 0.1206 0.9884
5.000 0.5852 0.01678 0.00843 -0.0025 0.1108 0.9937
5.250 0.6230 0.01736 0.00903 -0.0049 0.1031 0.9976
5.500 0.6476 0.01799 0.00957 -0.0051 0.0975 1.0000
5.750 0.6576 0.01836 0.00996 -0.0022 0.0942 1.0000
6.000 0.6701 0.01868 0.01030 0.0003 0.0903 1.0000
6.250 0.6865 0.01921 0.01075 0.0021 0.0865 1.0000
6.500 0.7056 0.02006 0.01159 0.0035 0.0827 1.0000
6.750 0.7265 0.02057 0.01215 0.0047 0.0786 1.0000
7.000 0.7482 0.02128 0.01278 0.0056 0.0748 1.0000
7.250 0.7706 0.02226 0.01384 0.0064 0.0711 1.0000
7.500 0.7934 0.02293 0.01457 0.0072 0.0674 1.0000
7.750 0.8166 0.02412 0.01563 0.0075 0.0640 1.0000
8.000 0.8389 0.02506 0.01680 0.0085 0.0610 1.0000
8.250 0.8616 0.02604 0.01789 0.0092 0.0582 1.0000
8.500 0.8847 0.02722 0.01900 0.0096 0.0560 1.0000
8.750 0.9050 0.02892 0.02096 0.0106 0.0537 1.0000
9.000 0.9250 0.03020 0.02248 0.0116 0.0513 1.0000
9.250 0.9463 0.03123 0.02354 0.0123 0.0495 1.0000
9.500 0.9672 0.03292 0.02522 0.0127 0.0482 1.0000
9.750 0.9806 0.03547 0.02816 0.0143 0.0471 1.0000
10.000 0.9902 0.03820 0.03137 0.0164 0.0463 1.0000
10.250 0.9954 0.04143 0.03504 0.0186 0.0457 1.0000
10.500 0.9950 0.04513 0.03916 0.0211 0.0454 1.0000
10.750 0.9877 0.04927 0.04371 0.0239 0.0454 1.0000
11.000 0.9734 0.05359 0.04839 0.0267 0.0456 1.0000
11.250 0.9512 0.05766 0.05273 0.0300 0.0458 1.0000
11.500 0.9250 0.06211 0.05742 0.0320 0.0461 1.0000
11.750 0.8996 0.06711 0.06261 0.0321 0.0465 1.0000
12.000 0.8750 0.07278 0.06843 0.0305 0.0469 1.0000
12.250 0.8539 0.07888 0.07463 0.0279 0.0473 1.0000
12.500 0.8400 0.08486 0.08066 0.0253 0.0476 1.0000
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Polar data table (+)
Polar graphs
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