NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 200,000 Max Cl/Cd: 35.07 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20412-il-200000.txt Download as CSV file: xf-sc20412-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0412 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 -0.7652 0.08736 0.08303 -0.0383 1.0000 0.0524
-12.250 -0.7841 0.08016 0.07577 -0.0422 1.0000 0.0518
-12.000 -0.8113 0.07273 0.06823 -0.0462 1.0000 0.0512
-11.750 -0.8435 0.06577 0.06110 -0.0493 1.0000 0.0504
-11.500 -0.8756 0.05980 0.05491 -0.0507 1.0000 0.0498
-11.250 -0.9040 0.05501 0.04988 -0.0503 1.0000 0.0494
-11.000 -0.9243 0.05067 0.04524 -0.0497 1.0000 0.0493
-10.750 -0.9332 0.04664 0.04088 -0.0489 1.0000 0.0494
-10.500 -0.9347 0.04297 0.03686 -0.0479 1.0000 0.0497
-10.250 -0.9301 0.03973 0.03324 -0.0469 1.0000 0.0503
-10.000 -0.9208 0.03688 0.03002 -0.0459 1.0000 0.0511
-9.750 -0.9080 0.03446 0.02720 -0.0450 1.0000 0.0521
-9.500 -0.8925 0.03215 0.02455 -0.0443 1.0000 0.0534
-9.250 -0.8728 0.03066 0.02312 -0.0437 1.0000 0.0550
-9.000 -0.8524 0.02963 0.02205 -0.0430 1.0000 0.0568
-8.750 -0.8321 0.02835 0.02060 -0.0423 1.0000 0.0588
-8.500 -0.8111 0.02710 0.01910 -0.0416 1.0000 0.0606
-8.250 -0.7908 0.02545 0.01736 -0.0407 1.0000 0.0626
-8.000 -0.7694 0.02459 0.01656 -0.0400 1.0000 0.0650
-7.750 -0.7476 0.02380 0.01571 -0.0393 1.0000 0.0677
-7.500 -0.7253 0.02303 0.01479 -0.0385 1.0000 0.0703
-7.250 -0.7046 0.02182 0.01361 -0.0375 1.0000 0.0731
-7.000 -0.6826 0.02117 0.01301 -0.0368 1.0000 0.0764
-6.750 -0.6601 0.02056 0.01235 -0.0361 1.0000 0.0798
-6.500 -0.6381 0.01972 0.01148 -0.0352 1.0000 0.0833
-6.250 -0.6159 0.01902 0.01088 -0.0347 1.0000 0.0875
-6.000 -0.5925 0.01851 0.01034 -0.0342 1.0000 0.0923
-5.750 -0.5692 0.01771 0.00961 -0.0338 1.0000 0.0974
-5.500 -0.5447 0.01717 0.00912 -0.0338 1.0000 0.1040
-5.250 -0.5191 0.01651 0.00850 -0.0340 1.0000 0.1118
-5.000 -0.4927 0.01602 0.00805 -0.0343 1.0000 0.1220
-4.750 -0.4641 0.01537 0.00752 -0.0353 1.0000 0.1377
-4.500 -0.4321 0.01456 0.00697 -0.0372 1.0000 0.1684
-4.250 -0.3882 0.01289 0.00615 -0.0427 1.0000 0.3079
-4.000 -0.3491 0.01186 0.00650 -0.0459 1.0000 0.5723
-3.750 -0.3257 0.01229 0.00697 -0.0448 1.0000 0.6184
-3.500 -0.3019 0.01273 0.00738 -0.0438 1.0000 0.6439
-3.250 -0.2799 0.01324 0.00786 -0.0424 1.0000 0.6610
-3.000 -0.2605 0.01381 0.00844 -0.0404 1.0000 0.6739
-2.750 -0.2426 0.01438 0.00904 -0.0381 1.0000 0.6834
-2.500 -0.2188 0.01479 0.00940 -0.0374 1.0000 0.6954
-2.250 -0.1985 0.01541 0.01008 -0.0353 0.9981 0.7023
-2.000 -0.1604 0.01582 0.01044 -0.0372 0.9943 0.7139
-1.750 -0.1346 0.01646 0.01115 -0.0357 0.9886 0.7209
-1.500 -0.1011 0.01700 0.01169 -0.0362 0.9840 0.7333
-1.250 -0.0776 0.01762 0.01237 -0.0339 0.9776 0.7416
-1.000 -0.0453 0.01795 0.01271 -0.0344 0.9727 0.7519
-0.750 -0.0152 0.01823 0.01302 -0.0340 0.9672 0.7581
-0.500 0.0295 0.01811 0.01288 -0.0378 0.9603 0.7663
-0.250 0.0672 0.01801 0.01280 -0.0388 0.9535 0.7692
0.000 0.1040 0.01784 0.01266 -0.0401 0.9455 0.7725
0.250 0.1555 0.01741 0.01225 -0.0442 0.9385 0.7761
0.500 0.2095 0.01672 0.01157 -0.0487 0.9278 0.7797
0.750 0.2491 0.01628 0.01115 -0.0509 0.9169 0.7832
1.000 0.2820 0.01586 0.01077 -0.0508 0.9059 0.7852
1.250 0.3138 0.01544 0.01038 -0.0506 0.8918 0.7875
1.500 0.3422 0.01513 0.01009 -0.0500 0.8744 0.7902
1.750 0.3715 0.01484 0.00982 -0.0498 0.8532 0.7931
2.000 0.4030 0.01456 0.00951 -0.0501 0.8273 0.7957
2.250 0.4370 0.01436 0.00925 -0.0513 0.7934 0.7991
2.500 0.4608 0.01420 0.00901 -0.0496 0.7504 0.8007
2.750 0.4846 0.01422 0.00879 -0.0480 0.6765 0.8024
3.000 0.5012 0.01498 0.00868 -0.0454 0.4915 0.8044
3.250 0.5170 0.01631 0.00904 -0.0437 0.3065 0.8066
3.500 0.5392 0.01732 0.00943 -0.0433 0.2026 0.8089
3.750 0.5657 0.01803 0.00984 -0.0436 0.1628 0.8113
4.000 0.5947 0.01869 0.01034 -0.0444 0.1415 0.8142
4.250 0.6209 0.01926 0.01080 -0.0444 0.1279 0.8165
4.500 0.6456 0.01958 0.01114 -0.0438 0.1182 0.8184
4.750 0.6698 0.02017 0.01169 -0.0431 0.1104 0.8207
5.000 0.6961 0.02059 0.01211 -0.0429 0.1034 0.8232
5.250 0.7230 0.02135 0.01282 -0.0431 0.0975 0.8257
5.500 0.7522 0.02180 0.01331 -0.0436 0.0917 0.8281
5.750 0.7814 0.02286 0.01423 -0.0444 0.0865 0.8304
6.000 0.8093 0.02327 0.01477 -0.0445 0.0822 0.8324
6.250 0.8343 0.02379 0.01530 -0.0440 0.0780 0.8344
6.500 0.8598 0.02496 0.01647 -0.0438 0.0744 0.8365
6.750 0.8862 0.02558 0.01723 -0.0435 0.0708 0.8389
7.000 0.9129 0.02626 0.01792 -0.0436 0.0674 0.8418
7.250 0.9409 0.02785 0.01952 -0.0441 0.0646 0.8448
7.500 0.9682 0.02880 0.02070 -0.0442 0.0618 0.8474
7.750 0.9916 0.02957 0.02158 -0.0435 0.0593 0.8496
8.000 1.0158 0.03063 0.02259 -0.0432 0.0572 0.8520
8.250 1.0381 0.03248 0.02472 -0.0425 0.0554 0.8549
8.500 1.0600 0.03421 0.02681 -0.0417 0.0538 0.8581
8.750 1.0824 0.03610 0.02898 -0.0413 0.0522 0.8612
9.000 1.1038 0.03742 0.03041 -0.0407 0.0509 0.8637
9.250 1.1241 0.03867 0.03167 -0.0400 0.0496 0.8663
9.500 1.1377 0.04160 0.03489 -0.0387 0.0485 0.8691
9.750 1.1447 0.04465 0.03851 -0.0364 0.0477 0.8722
10.000 1.1471 0.04864 0.04303 -0.0340 0.0472 0.8755
10.250 1.1424 0.05308 0.04795 -0.0312 0.0471 0.8785
10.500 1.1302 0.05761 0.05290 -0.0280 0.0472 0.8815
10.750 1.1134 0.06227 0.05790 -0.0250 0.0474 0.8846
11.000 1.0918 0.06639 0.06228 -0.0218 0.0477 0.8881
11.250 1.0704 0.07113 0.06722 -0.0204 0.0480 0.8914
11.500 1.0500 0.07596 0.07222 -0.0200 0.0483 0.8943
11.750 1.0390 0.08086 0.07720 -0.0204 0.0487 0.8973
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