NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 100,000 Max Cl/Cd: 29.31 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20410-il-100000-n5.txt Download as CSV file: xf-sc20410-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA SC(2)-0410 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.7083 0.10090 0.09518 -0.0161 1.0000 0.0343
-11.500 -0.7285 0.08971 0.08398 -0.0231 1.0000 0.0341
-11.250 -0.7559 0.07911 0.07329 -0.0310 1.0000 0.0338
-11.000 -0.7831 0.07113 0.06517 -0.0365 1.0000 0.0336
-10.750 -0.8079 0.06495 0.05882 -0.0396 1.0000 0.0334
-10.500 -0.8303 0.06003 0.05369 -0.0407 1.0000 0.0334
-10.250 -0.8481 0.05551 0.04890 -0.0413 1.0000 0.0334
-10.000 -0.8587 0.05086 0.04385 -0.0415 1.0000 0.0337
-9.750 -0.8638 0.04625 0.03863 -0.0414 1.0000 0.0344
-9.500 -0.8508 0.04426 0.03660 -0.0412 1.0000 0.0352
-9.250 -0.8368 0.04238 0.03458 -0.0409 1.0000 0.0362
-9.000 -0.8223 0.04017 0.03213 -0.0406 1.0000 0.0373
-8.750 -0.8070 0.03755 0.02917 -0.0403 1.0000 0.0383
-8.500 -0.7897 0.03495 0.02617 -0.0398 1.0000 0.0394
-8.250 -0.7704 0.03255 0.02335 -0.0393 1.0000 0.0408
-8.000 -0.7497 0.03060 0.02117 -0.0388 1.0000 0.0422
-7.750 -0.7282 0.02946 0.02002 -0.0385 1.0000 0.0442
-7.500 -0.7060 0.02829 0.01870 -0.0380 1.0000 0.0470
-7.250 -0.6832 0.02696 0.01709 -0.0374 1.0000 0.0499
-7.000 -0.6612 0.02564 0.01580 -0.0368 1.0000 0.0523
-6.750 -0.6384 0.02474 0.01489 -0.0364 1.0000 0.0559
-6.500 -0.6149 0.02384 0.01379 -0.0357 1.0000 0.0601
-6.250 -0.5924 0.02282 0.01286 -0.0353 1.0000 0.0642
-6.000 -0.5690 0.02204 0.01205 -0.0348 1.0000 0.0692
-5.750 -0.5456 0.02119 0.01117 -0.0343 1.0000 0.0742
-5.500 -0.5219 0.02042 0.01044 -0.0340 1.0000 0.0802
-5.250 -0.4975 0.01977 0.00971 -0.0336 1.0000 0.0862
-5.000 -0.4731 0.01898 0.00902 -0.0335 1.0000 0.0942
-4.750 -0.4479 0.01832 0.00837 -0.0334 1.0000 0.1034
-4.500 -0.4222 0.01771 0.00781 -0.0335 1.0000 0.1165
-4.250 -0.3960 0.01703 0.00730 -0.0338 1.0000 0.1386
-4.000 -0.3688 0.01624 0.00682 -0.0344 1.0000 0.1858
-3.750 -0.3383 0.01499 0.00627 -0.0364 1.0000 0.3179
-3.500 -0.3153 0.01417 0.00670 -0.0356 1.0000 0.5266
-3.250 -0.2942 0.01450 0.00719 -0.0335 1.0000 0.6146
-3.000 -0.2698 0.01477 0.00741 -0.0325 1.0000 0.6507
-2.750 -0.2455 0.01505 0.00762 -0.0315 1.0000 0.6757
-2.500 -0.2253 0.01546 0.00802 -0.0293 1.0000 0.6969
-2.250 -0.2064 0.01595 0.00851 -0.0268 1.0000 0.7191
-2.000 -0.1886 0.01641 0.00897 -0.0240 1.0000 0.7381
-1.750 -0.1736 0.01680 0.00939 -0.0206 1.0000 0.7509
-1.500 -0.1547 0.01703 0.00962 -0.0185 1.0000 0.7616
-1.250 -0.1299 0.01716 0.00970 -0.0181 1.0000 0.7722
-1.000 -0.1108 0.01730 0.00985 -0.0162 1.0000 0.7787
-0.750 -0.0825 0.01736 0.00988 -0.0169 0.9997 0.7861
-0.500 -0.0466 0.01736 0.00987 -0.0188 0.9946 0.7891
-0.250 -0.0109 0.01735 0.00986 -0.0207 0.9884 0.7919
0.000 0.0272 0.01737 0.00989 -0.0232 0.9834 0.7953
0.250 0.0639 0.01734 0.00989 -0.0254 0.9763 0.7990
0.500 0.1071 0.01728 0.00985 -0.0290 0.9687 0.8019
0.750 0.1495 0.01715 0.00979 -0.0318 0.9583 0.8038
1.000 0.1916 0.01695 0.00967 -0.0344 0.9454 0.8057
1.250 0.2387 0.01659 0.00938 -0.0377 0.9287 0.8074
1.500 0.2782 0.01620 0.00907 -0.0392 0.9030 0.8093
1.750 0.3163 0.01584 0.00877 -0.0404 0.8723 0.8118
2.000 0.3532 0.01553 0.00848 -0.0412 0.8303 0.8144
2.250 0.3874 0.01536 0.00822 -0.0416 0.7692 0.8167
2.500 0.4152 0.01538 0.00800 -0.0404 0.6734 0.8187
2.750 0.4363 0.01613 0.00786 -0.0382 0.4798 0.8210
3.000 0.4562 0.01726 0.00817 -0.0369 0.3146 0.8237
3.250 0.4797 0.01823 0.00854 -0.0367 0.2035 0.8262
3.500 0.5059 0.01897 0.00897 -0.0369 0.1523 0.8288
3.750 0.5337 0.01960 0.00947 -0.0373 0.1256 0.8315
4.000 0.5579 0.02015 0.00998 -0.0366 0.1103 0.8338
4.250 0.5828 0.02069 0.01052 -0.0361 0.0986 0.8365
4.500 0.6081 0.02135 0.01117 -0.0358 0.0906 0.8395
4.750 0.6347 0.02198 0.01183 -0.0358 0.0829 0.8424
5.000 0.6616 0.02280 0.01266 -0.0360 0.0768 0.8453
5.250 0.6875 0.02350 0.01341 -0.0358 0.0709 0.8479
5.500 0.7117 0.02438 0.01429 -0.0353 0.0660 0.8504
5.750 0.7377 0.02517 0.01522 -0.0350 0.0610 0.8533
6.000 0.7632 0.02605 0.01607 -0.0350 0.0568 0.8566
6.250 0.7902 0.02723 0.01742 -0.0350 0.0530 0.8601
6.500 0.8152 0.02817 0.01853 -0.0346 0.0493 0.8634
6.750 0.8386 0.02923 0.01959 -0.0342 0.0469 0.8668
7.000 0.8633 0.03090 0.02151 -0.0337 0.0449 0.8704
7.250 0.8881 0.03267 0.02362 -0.0334 0.0427 0.8741
7.500 0.9113 0.03409 0.02528 -0.0330 0.0406 0.8777
7.750 0.9324 0.03521 0.02649 -0.0324 0.0390 0.8813
8.000 0.9520 0.03733 0.02893 -0.0315 0.0376 0.8855
8.250 0.9689 0.04039 0.03256 -0.0304 0.0365 0.8901
8.500 0.9807 0.04361 0.03633 -0.0287 0.0357 0.8946
8.750 0.9891 0.04719 0.04042 -0.0270 0.0351 0.8997
9.000 0.9937 0.05126 0.04499 -0.0255 0.0346 0.9052
9.250 0.9915 0.05547 0.04966 -0.0234 0.0343 0.9107
9.500 0.9849 0.05998 0.05459 -0.0217 0.0340 0.9170
9.750 0.9714 0.06469 0.05965 -0.0201 0.0338 0.9241
10.250 0.9116 0.07697 0.07253 -0.0199 0.0342 0.9478
10.500 0.8658 0.08967 0.08546 -0.0292 0.0351 0.9980
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Polar data table (+)
Polar graphs
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