NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 1,000,000 Max Cl/Cd: 71.87 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20410-il-1000000.txt Download as CSV file: xf-sc20410-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -1.1006 0.07823 0.07575 -0.0242 1.0000 0.0134
-15.500 -1.1383 0.06631 0.06358 -0.0325 1.0000 0.0133
-15.250 -1.1607 0.05879 0.05587 -0.0372 1.0000 0.0133
-15.000 -1.1764 0.05314 0.05005 -0.0402 1.0000 0.0134
-14.750 -1.1866 0.04870 0.04546 -0.0421 1.0000 0.0134
-14.500 -1.1939 0.04491 0.04153 -0.0433 1.0000 0.0135
-14.250 -1.1978 0.04170 0.03819 -0.0440 1.0000 0.0136
-14.000 -1.1994 0.03887 0.03522 -0.0444 1.0000 0.0137
-13.750 -1.1989 0.03637 0.03259 -0.0444 1.0000 0.0138
-13.500 -1.1964 0.03417 0.03026 -0.0442 1.0000 0.0139
-13.250 -1.1925 0.03217 0.02814 -0.0438 1.0000 0.0140
-13.000 -1.1874 0.03043 0.02628 -0.0430 1.0000 0.0142
-12.750 -1.1811 0.02892 0.02466 -0.0421 1.0000 0.0143
-12.500 -1.1678 0.02752 0.02314 -0.0421 1.0000 0.0145
-12.250 -1.1521 0.02621 0.02171 -0.0422 1.0000 0.0147
-12.000 -1.1351 0.02498 0.02037 -0.0421 1.0000 0.0149
-11.750 -1.1171 0.02382 0.01909 -0.0419 1.0000 0.0150
-11.500 -1.0977 0.02279 0.01795 -0.0416 1.0000 0.0151
-11.250 -1.0773 0.02184 0.01690 -0.0414 1.0000 0.0153
-11.000 -1.0559 0.02100 0.01597 -0.0412 1.0000 0.0154
-10.750 -1.0371 0.01952 0.01435 -0.0409 1.0000 0.0156
-10.500 -1.0166 0.01822 0.01296 -0.0408 1.0000 0.0159
-10.250 -0.9939 0.01733 0.01201 -0.0407 1.0000 0.0163
-10.000 -0.9700 0.01664 0.01127 -0.0407 1.0000 0.0166
-9.750 -0.9454 0.01604 0.01063 -0.0407 1.0000 0.0170
-9.500 -0.9204 0.01547 0.01003 -0.0407 1.0000 0.0174
-9.250 -0.8951 0.01494 0.00945 -0.0407 1.0000 0.0178
-9.000 -0.8695 0.01444 0.00890 -0.0408 1.0000 0.0183
-8.750 -0.8436 0.01402 0.00844 -0.0408 1.0000 0.0188
-8.500 -0.8175 0.01355 0.00793 -0.0408 1.0000 0.0192
-8.250 -0.7910 0.01283 0.00718 -0.0412 1.0000 0.0202
-8.000 -0.7645 0.01242 0.00676 -0.0413 1.0000 0.0210
-7.750 -0.7380 0.01208 0.00641 -0.0414 1.0000 0.0220
-7.500 -0.7114 0.01177 0.00607 -0.0414 1.0000 0.0230
-7.250 -0.6842 0.01130 0.00561 -0.0416 1.0000 0.0250
-7.000 -0.6577 0.01104 0.00536 -0.0416 1.0000 0.0272
-6.750 -0.6308 0.01071 0.00503 -0.0417 1.0000 0.0301
-6.500 -0.6044 0.01049 0.00484 -0.0417 1.0000 0.0330
-6.250 -0.5779 0.01027 0.00461 -0.0416 1.0000 0.0355
-6.000 -0.5513 0.01003 0.00441 -0.0417 1.0000 0.0387
-5.750 -0.5254 0.00990 0.00428 -0.0415 1.0000 0.0410
-5.500 -0.4986 0.00967 0.00406 -0.0415 1.0000 0.0441
-5.250 -0.4641 0.00944 0.00386 -0.0432 0.9992 0.0476
-5.000 -0.4296 0.00927 0.00369 -0.0447 0.9982 0.0501
-4.750 -0.3946 0.00898 0.00343 -0.0465 0.9972 0.0557
-4.500 -0.3594 0.00879 0.00326 -0.0482 0.9961 0.0602
-4.250 -0.3237 0.00853 0.00307 -0.0501 0.9951 0.0700
-4.000 -0.2879 0.00827 0.00289 -0.0521 0.9943 0.0840
-3.750 -0.2528 0.00796 0.00270 -0.0539 0.9930 0.1082
-3.500 -0.2174 0.00752 0.00249 -0.0559 0.9915 0.1618
-3.250 -0.1805 0.00696 0.00228 -0.0584 0.9902 0.2475
-3.000 -0.1418 0.00629 0.00204 -0.0615 0.9890 0.3628
-2.750 -0.1011 0.00541 0.00178 -0.0651 0.9881 0.5283
-2.500 -0.0621 0.00514 0.00174 -0.0676 0.9862 0.6049
-2.250 -0.0237 0.00505 0.00168 -0.0698 0.9840 0.6269
-2.000 0.0104 0.00499 0.00164 -0.0710 0.9772 0.6414
-1.750 0.0457 0.00496 0.00163 -0.0724 0.9709 0.6532
-1.500 0.0769 0.00495 0.00161 -0.0729 0.9593 0.6602
-1.250 0.1063 0.00498 0.00163 -0.0729 0.9439 0.6682
-1.000 0.1342 0.00503 0.00166 -0.0725 0.9264 0.6766
-0.750 0.1613 0.00513 0.00170 -0.0720 0.9034 0.6829
-0.250 0.2165 0.00531 0.00173 -0.0713 0.8522 0.6921
0.000 0.2443 0.00543 0.00175 -0.0710 0.8244 0.6951
0.250 0.2717 0.00560 0.00178 -0.0706 0.7845 0.6988
0.500 0.2994 0.00582 0.00183 -0.0704 0.7396 0.7029
0.750 0.3268 0.00610 0.00188 -0.0702 0.6762 0.7065
1.000 0.3524 0.00669 0.00198 -0.0697 0.5444 0.7095
1.250 0.3780 0.00744 0.00217 -0.0695 0.3975 0.7116
1.500 0.4050 0.00796 0.00233 -0.0695 0.3018 0.7135
2.000 0.4598 0.00885 0.00264 -0.0696 0.1587 0.7173
2.250 0.4878 0.00917 0.00279 -0.0697 0.1202 0.7192
2.500 0.5159 0.00947 0.00295 -0.0698 0.0903 0.7209
2.750 0.5442 0.00970 0.00309 -0.0699 0.0748 0.7225
3.000 0.5725 0.00989 0.00325 -0.0699 0.0650 0.7246
3.250 0.6006 0.01011 0.00343 -0.0699 0.0577 0.7263
3.500 0.6289 0.01028 0.00361 -0.0700 0.0537 0.7280
3.750 0.6571 0.01048 0.00379 -0.0700 0.0499 0.7297
4.000 0.6850 0.01074 0.00404 -0.0700 0.0459 0.7316
4.250 0.7133 0.01090 0.00421 -0.0700 0.0438 0.7334
4.500 0.7413 0.01111 0.00440 -0.0700 0.0409 0.7353
4.750 0.7690 0.01140 0.00468 -0.0699 0.0378 0.7371
5.000 0.7971 0.01158 0.00486 -0.0700 0.0354 0.7386
5.250 0.8243 0.01191 0.00518 -0.0698 0.0316 0.7411
5.500 0.8521 0.01207 0.00537 -0.0698 0.0294 0.7433
5.750 0.8789 0.01246 0.00575 -0.0696 0.0260 0.7454
6.000 0.9065 0.01268 0.00599 -0.0695 0.0244 0.7475
6.250 0.9336 0.01299 0.00630 -0.0693 0.0228 0.7497
6.500 0.9597 0.01351 0.00684 -0.0690 0.0213 0.7520
6.750 0.9867 0.01384 0.00721 -0.0688 0.0206 0.7540
7.000 1.0134 0.01421 0.00761 -0.0686 0.0199 0.7561
7.250 1.0397 0.01458 0.00803 -0.0683 0.0192 0.7586
7.500 1.0657 0.01500 0.00850 -0.0679 0.0186 0.7610
7.750 1.0909 0.01557 0.00911 -0.0675 0.0181 0.7634
8.000 1.1141 0.01650 0.01013 -0.0667 0.0174 0.7660
8.250 1.1391 0.01706 0.01076 -0.0662 0.0172 0.7686
8.500 1.1642 0.01761 0.01137 -0.0658 0.0170 0.7710
8.750 1.1888 0.01817 0.01201 -0.0652 0.0168 0.7737
9.000 1.2132 0.01873 0.01266 -0.0647 0.0164 0.7764
9.250 1.2374 0.01931 0.01332 -0.0641 0.0160 0.7793
9.500 1.2609 0.01999 0.01408 -0.0634 0.0157 0.7823
9.750 1.2841 0.02069 0.01485 -0.0627 0.0155 0.7854
10.000 1.3067 0.02141 0.01566 -0.0620 0.0152 0.7885
10.250 1.3286 0.02219 0.01653 -0.0611 0.0150 0.7918
10.500 1.3495 0.02309 0.01753 -0.0602 0.0147 0.7952
10.750 1.3685 0.02424 0.01878 -0.0590 0.0145 0.7989
11.000 1.3844 0.02585 0.02054 -0.0574 0.0143 0.8022
11.250 1.3938 0.02835 0.02332 -0.0551 0.0140 0.8057
11.500 1.4070 0.03004 0.02522 -0.0532 0.0139 0.8094
11.750 1.4222 0.03127 0.02660 -0.0517 0.0138 0.8134
12.000 1.4353 0.03266 0.02815 -0.0499 0.0138 0.8173
12.250 1.4457 0.03418 0.02985 -0.0478 0.0137 0.8213
12.500 1.4531 0.03585 0.03171 -0.0454 0.0136 0.8257
12.750 1.4554 0.03774 0.03378 -0.0425 0.0135 0.8303
13.000 1.4491 0.03962 0.03585 -0.0383 0.0135 0.8350
13.250 1.4412 0.04192 0.03834 -0.0348 0.0134 0.8403
13.500 1.4327 0.04455 0.04114 -0.0321 0.0134 0.8457
13.750 1.4207 0.04781 0.04462 -0.0303 0.0133 0.8506
14.000 1.4062 0.05184 0.04884 -0.0296 0.0133 0.8559
14.250 1.3895 0.05678 0.05398 -0.0305 0.0132 0.8610
14.500 1.3647 0.06393 0.06137 -0.0338 0.0132 0.8655
14.750 1.3273 0.07550 0.07321 -0.0421 0.0133 0.8696
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