NASA SC(2)-0412 AIRFOIL (sc20412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA SC(2)-0412 AIRFOIL (sc20412-il) Reynolds number: 500,000 Max Cl/Cd: 63.01 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sc20412-il-500000-n5.txt Download as CSV file: xf-sc20412-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.500 -1.0548 0.12537 0.12198 -0.0068 1.0000 0.0173
-18.250 -1.0931 0.11326 0.10969 -0.0137 1.0000 0.0173
-18.000 -1.1247 0.10281 0.09906 -0.0196 1.0000 0.0173
-17.750 -1.1513 0.09353 0.08961 -0.0248 1.0000 0.0174
-17.500 -1.1732 0.08535 0.08126 -0.0295 1.0000 0.0174
-17.250 -1.1905 0.07821 0.07395 -0.0336 1.0000 0.0174
-17.000 -1.2049 0.07189 0.06749 -0.0371 1.0000 0.0175
-16.750 -1.2169 0.06624 0.06170 -0.0401 1.0000 0.0176
-16.500 -1.2261 0.06132 0.05666 -0.0425 1.0000 0.0177
-16.250 -1.2325 0.05706 0.05228 -0.0444 1.0000 0.0178
-16.000 -1.2367 0.05330 0.04841 -0.0458 1.0000 0.0180
-15.750 -1.2388 0.05003 0.04504 -0.0468 1.0000 0.0181
-15.500 -1.2392 0.04714 0.04205 -0.0475 1.0000 0.0183
-15.250 -1.2378 0.04454 0.03936 -0.0480 1.0000 0.0184
-15.000 -1.2347 0.04220 0.03692 -0.0482 1.0000 0.0186
-14.750 -1.2302 0.04006 0.03469 -0.0483 1.0000 0.0188
-14.500 -1.2246 0.03809 0.03263 -0.0483 1.0000 0.0191
-14.250 -1.2178 0.03627 0.03071 -0.0482 1.0000 0.0193
-14.000 -1.2098 0.03459 0.02894 -0.0479 1.0000 0.0196
-13.750 -1.2008 0.03303 0.02729 -0.0476 1.0000 0.0199
-13.500 -1.1911 0.03157 0.02573 -0.0472 1.0000 0.0202
-13.250 -1.1803 0.03022 0.02430 -0.0467 1.0000 0.0205
-13.000 -1.1688 0.02898 0.02297 -0.0461 1.0000 0.0208
-12.750 -1.1586 0.02768 0.02160 -0.0454 1.0000 0.0211
-12.500 -1.1477 0.02651 0.02040 -0.0446 1.0000 0.0215
-12.250 -1.1364 0.02551 0.01935 -0.0436 1.0000 0.0219
-12.000 -1.1247 0.02460 0.01839 -0.0424 1.0000 0.0223
-11.750 -1.1092 0.02373 0.01747 -0.0418 1.0000 0.0228
-11.500 -1.0923 0.02290 0.01659 -0.0414 1.0000 0.0234
-11.250 -1.0742 0.02213 0.01576 -0.0410 1.0000 0.0240
-11.000 -1.0551 0.02143 0.01498 -0.0406 1.0000 0.0246
-10.750 -1.0363 0.02063 0.01416 -0.0403 1.0000 0.0253
-10.500 -1.0158 0.01997 0.01349 -0.0401 1.0000 0.0261
-10.250 -0.9947 0.01939 0.01287 -0.0397 1.0000 0.0269
-10.000 -0.9732 0.01884 0.01228 -0.0394 1.0000 0.0277
-9.750 -0.9512 0.01832 0.01170 -0.0390 1.0000 0.0286
-9.500 -0.9291 0.01776 0.01112 -0.0387 1.0000 0.0294
-9.250 -0.9065 0.01724 0.01060 -0.0384 1.0000 0.0304
-9.000 -0.8834 0.01680 0.01014 -0.0381 1.0000 0.0315
-8.750 -0.8599 0.01638 0.00970 -0.0378 1.0000 0.0327
-8.500 -0.8362 0.01601 0.00928 -0.0376 1.0000 0.0338
-8.250 -0.8048 0.01550 0.00879 -0.0390 0.9988 0.0355
-8.000 -0.7720 0.01509 0.00837 -0.0405 0.9973 0.0372
-7.750 -0.7386 0.01470 0.00796 -0.0422 0.9956 0.0389
-7.500 -0.7048 0.01427 0.00753 -0.0439 0.9941 0.0407
-7.250 -0.6717 0.01389 0.00716 -0.0455 0.9923 0.0430
-7.000 -0.6391 0.01356 0.00681 -0.0469 0.9900 0.0451
-6.750 -0.6062 0.01318 0.00645 -0.0484 0.9879 0.0475
-6.500 -0.5727 0.01285 0.00613 -0.0500 0.9861 0.0504
-6.250 -0.5387 0.01256 0.00583 -0.0516 0.9844 0.0529
-6.000 -0.5042 0.01218 0.00549 -0.0534 0.9830 0.0567
-5.750 -0.4705 0.01190 0.00520 -0.0549 0.9811 0.0604
-5.500 -0.4379 0.01159 0.00492 -0.0562 0.9782 0.0645
-5.250 -0.4044 0.01130 0.00466 -0.0577 0.9755 0.0700
-5.000 -0.3701 0.01099 0.00442 -0.0593 0.9731 0.0779
-4.750 -0.3352 0.01070 0.00418 -0.0611 0.9708 0.0868
-4.500 -0.3019 0.01043 0.00395 -0.0625 0.9671 0.0979
-4.250 -0.2693 0.01014 0.00374 -0.0637 0.9623 0.1122
-4.000 -0.2350 0.00980 0.00352 -0.0654 0.9586 0.1346
-3.750 -0.2004 0.00942 0.00330 -0.0672 0.9552 0.1703
-3.500 -0.1677 0.00902 0.00309 -0.0686 0.9498 0.2145
-3.250 -0.1326 0.00849 0.00284 -0.0707 0.9454 0.2812
-3.000 -0.0957 0.00785 0.00256 -0.0734 0.9418 0.3726
-2.750 -0.0585 0.00711 0.00232 -0.0762 0.9372 0.4955
-2.500 -0.0256 0.00689 0.00234 -0.0773 0.9304 0.5666
-2.250 0.0050 0.00686 0.00234 -0.0776 0.9212 0.5911
-1.750 0.0640 0.00688 0.00237 -0.0778 0.8976 0.6205
-1.500 0.0932 0.00694 0.00243 -0.0778 0.8869 0.6347
-1.250 0.1221 0.00701 0.00245 -0.0776 0.8713 0.6449
-1.000 0.1498 0.00710 0.00247 -0.0772 0.8467 0.6523
-0.750 0.1783 0.00722 0.00246 -0.0770 0.8198 0.6598
-0.500 0.2064 0.00732 0.00253 -0.0767 0.7993 0.6649
-0.250 0.2343 0.00747 0.00257 -0.0764 0.7695 0.6702
0.000 0.2627 0.00764 0.00258 -0.0763 0.7346 0.6750
0.250 0.2905 0.00784 0.00258 -0.0760 0.6869 0.6775
0.500 0.3164 0.00823 0.00262 -0.0755 0.5967 0.6790
1.000 0.3673 0.00950 0.00295 -0.0748 0.3737 0.6821
1.250 0.3945 0.00994 0.00311 -0.0748 0.3039 0.6837
1.500 0.4218 0.01037 0.00327 -0.0748 0.2393 0.6855
1.750 0.4494 0.01074 0.00342 -0.0749 0.1912 0.6872
2.000 0.4775 0.01105 0.00357 -0.0750 0.1586 0.6890
2.250 0.5059 0.01128 0.00371 -0.0751 0.1383 0.6908
2.500 0.5344 0.01153 0.00387 -0.0752 0.1204 0.6927
2.750 0.5628 0.01177 0.00402 -0.0753 0.1067 0.6947
3.000 0.5908 0.01198 0.00420 -0.0753 0.0956 0.6965
3.250 0.6187 0.01221 0.00439 -0.0752 0.0853 0.6982
3.500 0.6466 0.01245 0.00459 -0.0752 0.0775 0.6998
3.750 0.6746 0.01267 0.00480 -0.0752 0.0718 0.7014
4.000 0.7024 0.01293 0.00503 -0.0752 0.0666 0.7031
4.250 0.7303 0.01316 0.00526 -0.0751 0.0630 0.7049
4.500 0.7582 0.01340 0.00550 -0.0751 0.0595 0.7067
4.750 0.7856 0.01370 0.00576 -0.0750 0.0561 0.7085
5.000 0.8135 0.01393 0.00601 -0.0750 0.0535 0.7103
5.250 0.8409 0.01421 0.00628 -0.0749 0.0509 0.7120
5.500 0.8680 0.01452 0.00658 -0.0747 0.0483 0.7136
5.750 0.8951 0.01477 0.00687 -0.0745 0.0461 0.7152
6.000 0.9219 0.01507 0.00719 -0.0743 0.0438 0.7171
6.250 0.9483 0.01542 0.00754 -0.0740 0.0417 0.7191
6.500 0.9751 0.01571 0.00788 -0.0738 0.0398 0.7211
6.750 1.0016 0.01603 0.00821 -0.0736 0.0377 0.7231
7.000 1.0277 0.01642 0.00860 -0.0732 0.0360 0.7253
7.250 1.0539 0.01677 0.00900 -0.0729 0.0345 0.7275
7.500 1.0800 0.01714 0.00938 -0.0726 0.0330 0.7297
7.750 1.1055 0.01755 0.00980 -0.0723 0.0316 0.7315
8.000 1.1307 0.01796 0.01027 -0.0718 0.0304 0.7333
8.250 1.1559 0.01837 0.01073 -0.0713 0.0291 0.7351
8.500 1.1807 0.01879 0.01119 -0.0708 0.0279 0.7370
8.750 1.2049 0.01930 0.01172 -0.0702 0.0268 0.7392
9.000 1.2290 0.01980 0.01229 -0.0696 0.0261 0.7416
9.250 1.2529 0.02031 0.01286 -0.0690 0.0252 0.7441
9.500 1.2765 0.02085 0.01345 -0.0684 0.0245 0.7465
9.750 1.2997 0.02141 0.01405 -0.0677 0.0238 0.7486
10.000 1.3220 0.02201 0.01471 -0.0668 0.0232 0.7506
10.250 1.3429 0.02274 0.01549 -0.0658 0.0226 0.7526
10.500 1.3645 0.02337 0.01622 -0.0648 0.0222 0.7549
10.750 1.3853 0.02405 0.01700 -0.0638 0.0217 0.7573
11.000 1.4055 0.02476 0.01780 -0.0627 0.0212 0.7598
11.250 1.4251 0.02550 0.01862 -0.0615 0.0208 0.7624
11.500 1.4440 0.02625 0.01945 -0.0603 0.0204 0.7649
11.750 1.4619 0.02702 0.02031 -0.0589 0.0200 0.7672
12.000 1.4782 0.02787 0.02123 -0.0573 0.0196 0.7696
12.250 1.4920 0.02886 0.02230 -0.0555 0.0193 0.7722
12.500 1.5035 0.02992 0.02346 -0.0532 0.0189 0.7750
12.750 1.5136 0.03087 0.02453 -0.0507 0.0187 0.7782
13.000 1.5210 0.03193 0.02571 -0.0479 0.0185 0.7815
13.250 1.5287 0.03311 0.02703 -0.0455 0.0183 0.7844
13.500 1.5354 0.03442 0.02848 -0.0431 0.0181 0.7874
13.750 1.5410 0.03586 0.03006 -0.0408 0.0179 0.7906
14.000 1.5454 0.03746 0.03179 -0.0387 0.0177 0.7938
14.250 1.5486 0.03923 0.03370 -0.0368 0.0175 0.7971
14.500 1.5506 0.04121 0.03581 -0.0351 0.0174 0.8001
14.750 1.5510 0.04341 0.03817 -0.0336 0.0172 0.8033
15.000 1.5500 0.04590 0.04081 -0.0325 0.0171 0.8069
15.250 1.5472 0.04875 0.04380 -0.0317 0.0170 0.8107
15.500 1.5425 0.05201 0.04721 -0.0315 0.0168 0.8145
15.750 1.5357 0.05575 0.05111 -0.0317 0.0167 0.8177
16.000 1.5258 0.06016 0.05569 -0.0326 0.0167 0.8210
16.250 1.5127 0.06544 0.06114 -0.0345 0.0166 0.8242
16.500 1.4955 0.07191 0.06780 -0.0375 0.0165 0.8273
16.750 1.4729 0.07996 0.07607 -0.0420 0.0165 0.8299
17.250 1.3991 0.10371 0.10031 -0.0565 0.0166 0.8326
17.500 1.3421 0.12020 0.11707 -0.0664 0.0167 0.8326
|
Polar data table (+)
Polar graphs
<< Back to NASA SC(2)-0412 AIRFOIL (sc20412-il)