NASA SC(2)-0410 AIRFOIL (sc20410-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA SC(2)-0410 AIRFOIL (sc20410-il) Reynolds number: 500,000 Max Cl/Cd: 53.96 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sc20410-il-500000.txt Download as CSV file: xf-sc20410-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.9053 0.06052 0.05751 -0.0398 1.0000 0.0215
-12.000 -0.9528 0.05127 0.04791 -0.0439 1.0000 0.0212
-11.750 -0.9904 0.04453 0.04079 -0.0446 1.0000 0.0210
-11.500 -1.0113 0.03987 0.03579 -0.0440 1.0000 0.0209
-11.250 -1.0141 0.03607 0.03164 -0.0439 1.0000 0.0210
-11.000 -1.0079 0.03315 0.02842 -0.0434 1.0000 0.0212
-10.750 -0.9964 0.03071 0.02571 -0.0429 1.0000 0.0214
-10.500 -0.9816 0.02860 0.02336 -0.0424 1.0000 0.0217
-10.250 -0.9643 0.02678 0.02131 -0.0420 1.0000 0.0220
-10.000 -0.9452 0.02519 0.01952 -0.0415 1.0000 0.0223
-9.750 -0.9248 0.02382 0.01798 -0.0411 1.0000 0.0227
-9.500 -0.9031 0.02272 0.01672 -0.0407 1.0000 0.0231
-9.250 -0.8824 0.02119 0.01503 -0.0402 1.0000 0.0237
-9.000 -0.8606 0.02003 0.01384 -0.0399 1.0000 0.0244
-8.750 -0.8372 0.01930 0.01308 -0.0396 1.0000 0.0251
-8.500 -0.8135 0.01855 0.01228 -0.0394 1.0000 0.0258
-8.250 -0.7894 0.01781 0.01148 -0.0391 1.0000 0.0266
-8.000 -0.7651 0.01712 0.01071 -0.0388 1.0000 0.0275
-7.750 -0.7401 0.01659 0.01010 -0.0386 1.0000 0.0283
-7.500 -0.7160 0.01545 0.00897 -0.0387 1.0000 0.0300
-7.250 -0.6905 0.01498 0.00850 -0.0386 1.0000 0.0317
-7.000 -0.6648 0.01456 0.00803 -0.0385 1.0000 0.0338
-6.750 -0.6387 0.01384 0.00734 -0.0387 1.0000 0.0367
-6.500 -0.6128 0.01356 0.00706 -0.0386 1.0000 0.0399
-6.250 -0.5862 0.01304 0.00652 -0.0388 1.0000 0.0434
-6.000 -0.5599 0.01271 0.00622 -0.0388 1.0000 0.0468
-5.750 -0.5339 0.01249 0.00598 -0.0386 1.0000 0.0498
-5.500 -0.5062 0.01195 0.00545 -0.0391 1.0000 0.0539
-5.250 -0.4796 0.01170 0.00521 -0.0392 1.0000 0.0578
-5.000 -0.4531 0.01150 0.00499 -0.0391 1.0000 0.0612
-4.750 -0.4250 0.01110 0.00464 -0.0396 1.0000 0.0679
-4.500 -0.3982 0.01091 0.00445 -0.0397 1.0000 0.0737
-4.250 -0.3697 0.01058 0.00419 -0.0403 1.0000 0.0835
-4.000 -0.3407 0.01027 0.00394 -0.0409 1.0000 0.0973
-3.750 -0.3095 0.00985 0.00372 -0.0421 1.0000 0.1333
-3.500 -0.2717 0.00900 0.00342 -0.0453 1.0000 0.2544
-3.250 -0.2244 0.00768 0.00298 -0.0509 1.0000 0.4673
-3.000 -0.1891 0.00731 0.00313 -0.0528 1.0000 0.6080
-2.750 -0.1617 0.00743 0.00329 -0.0528 1.0000 0.6362
-2.500 -0.1326 0.00757 0.00342 -0.0531 0.9994 0.6551
-2.250 -0.0954 0.00762 0.00348 -0.0550 0.9965 0.6697
-2.000 -0.0572 0.00768 0.00357 -0.0570 0.9941 0.6811
-1.750 -0.0202 0.00767 0.00354 -0.0589 0.9894 0.6901
-1.500 0.0189 0.00770 0.00362 -0.0610 0.9857 0.6998
-1.250 0.0586 0.00773 0.00369 -0.0631 0.9816 0.7106
-1.000 0.0987 0.00771 0.00369 -0.0653 0.9756 0.7190
-0.750 0.1411 0.00757 0.00357 -0.0681 0.9709 0.7239
-0.500 0.1740 0.00751 0.00357 -0.0687 0.9605 0.7281
-0.250 0.2067 0.00749 0.00355 -0.0692 0.9466 0.7332
0.000 0.2378 0.00747 0.00350 -0.0695 0.9282 0.7378
0.250 0.2652 0.00745 0.00346 -0.0689 0.9064 0.7407
0.500 0.2920 0.00747 0.00345 -0.0682 0.8832 0.7429
0.750 0.3189 0.00752 0.00344 -0.0676 0.8538 0.7449
1.000 0.3456 0.00762 0.00342 -0.0669 0.8179 0.7471
1.250 0.3725 0.00777 0.00342 -0.0664 0.7718 0.7494
1.500 0.3988 0.00804 0.00342 -0.0658 0.7014 0.7515
1.750 0.4225 0.00877 0.00348 -0.0649 0.5468 0.7534
2.000 0.4463 0.00981 0.00372 -0.0646 0.3666 0.7551
2.250 0.4715 0.01052 0.00393 -0.0644 0.2450 0.7568
2.500 0.4974 0.01112 0.00417 -0.0642 0.1603 0.7584
2.750 0.5242 0.01158 0.00441 -0.0641 0.1135 0.7601
3.000 0.5516 0.01194 0.00466 -0.0641 0.0907 0.7619
3.250 0.5791 0.01230 0.00496 -0.0640 0.0786 0.7639
3.500 0.6072 0.01257 0.00519 -0.0641 0.0706 0.7660
3.750 0.6352 0.01288 0.00549 -0.0641 0.0645 0.7681
4.000 0.6634 0.01316 0.00575 -0.0642 0.0598 0.7701
4.250 0.6906 0.01361 0.00620 -0.0642 0.0551 0.7719
4.500 0.7182 0.01380 0.00643 -0.0641 0.0516 0.7736
4.750 0.7449 0.01416 0.00677 -0.0639 0.0476 0.7754
5.000 0.7716 0.01454 0.00721 -0.0636 0.0443 0.7773
5.250 0.7990 0.01482 0.00749 -0.0635 0.0409 0.7795
5.500 0.8248 0.01544 0.00812 -0.0632 0.0375 0.7821
5.750 0.8521 0.01579 0.00850 -0.0631 0.0347 0.7846
6.000 0.8783 0.01639 0.00906 -0.0629 0.0323 0.7869
6.250 0.9033 0.01705 0.00981 -0.0623 0.0306 0.7888
6.500 0.9293 0.01749 0.01032 -0.0620 0.0290 0.7909
6.750 0.9551 0.01794 0.01080 -0.0616 0.0276 0.7932
7.000 0.9796 0.01875 0.01163 -0.0611 0.0266 0.7958
7.250 1.0034 0.01987 0.01285 -0.0605 0.0257 0.7984
7.500 1.0288 0.02062 0.01371 -0.0601 0.0251 0.8012
7.750 1.0532 0.02147 0.01467 -0.0594 0.0245 0.8035
8.000 1.0769 0.02238 0.01571 -0.0587 0.0239 0.8058
8.250 1.1004 0.02333 0.01680 -0.0581 0.0233 0.8085
8.500 1.1236 0.02431 0.01789 -0.0574 0.0229 0.8115
8.750 1.1465 0.02535 0.01903 -0.0568 0.0224 0.8146
9.000 1.1683 0.02656 0.02033 -0.0560 0.0220 0.8176
9.250 1.1853 0.02891 0.02289 -0.0547 0.0215 0.8203
9.500 1.2025 0.03079 0.02507 -0.0533 0.0212 0.8235
9.750 1.2192 0.03259 0.02718 -0.0518 0.0209 0.8270
10.000 1.2322 0.03505 0.02997 -0.0501 0.0207 0.8305
10.250 1.2395 0.03810 0.03342 -0.0478 0.0205 0.8335
10.500 1.2392 0.04196 0.03772 -0.0449 0.0204 0.8367
10.750 1.2278 0.04681 0.04305 -0.0413 0.0204 0.8403
11.000 1.2038 0.05230 0.04898 -0.0372 0.0205 0.8443
11.250 1.1721 0.05686 0.05382 -0.0327 0.0205 0.8485
11.500 1.1395 0.06239 0.05963 -0.0311 0.0207 0.8524
11.750 1.1054 0.06961 0.06709 -0.0335 0.0208 0.8565
12.000 1.0678 0.08055 0.07825 -0.0419 0.0210 0.8601
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