NACA 66(3)-218 (naca663218-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(3)-218 (naca663218-il) Reynolds number: 200,000 Max Cl/Cd: 38.38 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca663218-il-200000.txt Download as CSV file: xf-naca663218-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(3)-218
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.3959 0.12020 0.11657 -0.0769 0.9806 0.0790
-13.750 -0.4744 0.10007 0.09644 -0.0969 0.9763 0.0855
-13.500 -0.5326 0.09039 0.08656 -0.1057 0.9723 0.0857
-13.250 -0.4237 0.09525 0.09163 -0.0972 0.9720 0.0889
-13.000 -0.4170 0.09063 0.08699 -0.1007 0.9682 0.0911
-12.750 -0.4544 0.07963 0.07590 -0.1097 0.9632 0.0930
-12.500 -0.4920 0.07160 0.06768 -0.1155 0.9586 0.0941
-12.250 -0.5281 0.06653 0.06241 -0.1168 0.9501 0.0955
-12.000 -0.6732 0.04889 0.04318 -0.1067 0.9348 0.0510
-11.750 -0.7377 0.04606 0.03944 -0.0949 0.9226 0.0462
-11.500 -0.7204 0.04349 0.03668 -0.0944 0.9188 0.0454
-11.250 -0.7064 0.04067 0.03362 -0.0934 0.9155 0.0451
-11.000 -0.7050 0.03944 0.03214 -0.0901 0.9102 0.0453
-10.750 -0.6972 0.03790 0.03034 -0.0877 0.9053 0.0455
-10.500 -0.6892 0.03682 0.02899 -0.0850 0.9013 0.0458
-10.250 -0.6581 0.03429 0.02621 -0.0863 0.8995 0.0460
-10.000 -0.5920 0.03097 0.02277 -0.0930 0.9003 0.0469
-9.750 -0.5504 0.02954 0.02129 -0.0953 0.8992 0.0479
-9.500 -0.5179 0.02862 0.02031 -0.0962 0.8975 0.0493
-9.250 -0.4881 0.02788 0.01954 -0.0969 0.8950 0.0509
-9.000 -0.4623 0.02731 0.01888 -0.0969 0.8922 0.0529
-8.750 -0.4287 0.02651 0.01806 -0.0978 0.8903 0.0547
-8.500 -0.4031 0.02582 0.01745 -0.0977 0.8880 0.0570
-8.250 -0.3832 0.02529 0.01693 -0.0969 0.8855 0.0593
-8.000 -0.3649 0.02484 0.01642 -0.0958 0.8833 0.0625
-7.750 -0.3520 0.02414 0.01577 -0.0940 0.8811 0.0664
-7.500 -0.3397 0.02374 0.01539 -0.0925 0.8781 0.0705
-7.250 -0.3309 0.02324 0.01490 -0.0903 0.8744 0.0758
-7.000 -0.3228 0.02274 0.01442 -0.0879 0.8713 0.0827
-6.750 -0.3172 0.02215 0.01390 -0.0851 0.8685 0.0971
-6.500 -0.3234 0.02117 0.01330 -0.0805 0.8658 0.1478
-6.250 -0.3456 0.02039 0.01308 -0.0735 0.8622 0.2422
-6.000 -0.3737 0.02070 0.01360 -0.0650 0.8569 0.2817
-5.750 -0.4048 0.02088 0.01395 -0.0550 0.8520 0.3175
-5.500 -0.4334 0.02062 0.01402 -0.0454 0.8490 0.3862
-5.250 -0.4560 0.01999 0.01407 -0.0365 0.8471 0.5061
-5.000 -0.5004 0.02242 0.01574 -0.0242 0.8413 0.3813
-4.750 -0.5286 0.02233 0.01599 -0.0148 0.8392 0.4469
-4.500 -0.5414 0.02235 0.01709 -0.0067 0.8369 0.6371
-4.250 -0.5337 0.02302 0.01771 -0.0030 0.8359 0.6857
-4.000 -0.5123 0.02407 0.01875 -0.0011 0.8344 0.7103
-3.750 -0.4845 0.02512 0.01974 -0.0002 0.8329 0.7274
-3.500 -0.4582 0.02624 0.02081 0.0010 0.8319 0.7406
-3.250 -0.4251 0.02765 0.02219 0.0014 0.8308 0.7549
-3.000 -0.3310 0.03267 0.02725 -0.0039 0.8307 0.7738
-2.750 -0.2825 0.03382 0.02830 -0.0066 0.8299 0.7855
-2.500 -0.2172 0.03465 0.02903 -0.0128 0.8297 0.7884
-2.250 -0.1423 0.03523 0.02950 -0.0211 0.8296 0.7897
-1.500 -0.2936 0.03503 0.02938 0.0182 0.8150 0.8214
-1.250 -0.2449 0.03536 0.02963 0.0145 0.8137 0.8225
-1.000 -0.2435 0.03574 0.03000 0.0189 0.8086 0.8258
-0.750 -0.2422 0.03579 0.03003 0.0229 0.8040 0.8303
-0.500 -0.2485 0.03483 0.02899 0.0274 0.7997 0.8385
-0.250 -0.2070 0.03492 0.02904 0.0249 0.7976 0.8395
0.000 -0.1608 0.03508 0.02914 0.0215 0.7961 0.8405
0.250 -0.1860 0.03497 0.02906 0.0299 0.7864 0.8445
0.500 -0.1596 0.03486 0.02890 0.0296 0.7830 0.8468
0.750 -0.1234 0.03471 0.02871 0.0277 0.7806 0.8485
1.000 -0.0835 0.03462 0.02858 0.0251 0.7790 0.8501
1.250 -0.1111 0.03399 0.02792 0.0325 0.7675 0.8554
1.500 -0.0761 0.03385 0.02777 0.0309 0.7648 0.8562
1.750 -0.0363 0.03379 0.02770 0.0287 0.7630 0.8570
2.000 0.0047 0.03378 0.02768 0.0262 0.7616 0.8577
2.250 -0.0093 0.03373 0.02764 0.0320 0.7493 0.8601
2.500 0.0297 0.03354 0.02745 0.0298 0.7471 0.8608
2.750 0.0706 0.03341 0.02733 0.0274 0.7457 0.8616
3.000 0.0649 0.03350 0.02743 0.0317 0.7335 0.8647
3.250 0.1033 0.03325 0.02720 0.0296 0.7312 0.8655
3.500 0.1446 0.03297 0.02694 0.0272 0.7297 0.8664
3.750 0.1470 0.03311 0.02709 0.0299 0.7177 0.8688
4.000 0.1869 0.03272 0.02674 0.0277 0.7152 0.8697
4.250 0.2297 0.03229 0.02635 0.0251 0.7137 0.8706
4.500 0.2351 0.03248 0.02657 0.0277 0.7018 0.8729
4.750 0.2732 0.03200 0.02616 0.0262 0.6994 0.8740
5.000 0.3158 0.03134 0.02556 0.0242 0.6977 0.8749
5.250 0.3605 0.03053 0.02483 0.0219 0.6960 0.8758
5.500 0.3670 0.03063 0.02499 0.0246 0.6835 0.8781
5.750 0.4120 0.02969 0.02415 0.0224 0.6820 0.8791
6.000 0.4526 0.02885 0.02340 0.0208 0.6796 0.8803
6.250 0.4719 0.02835 0.02298 0.0220 0.6681 0.8827
6.500 0.5737 0.02265 0.01740 0.0154 0.6662 0.8815
7.250 0.6209 0.02139 0.01636 0.0210 0.6179 0.8896
7.500 0.6309 0.02130 0.01633 0.0238 0.5892 0.8925
7.750 0.7008 0.01826 0.01253 0.0207 0.4665 0.8925
8.000 0.6882 0.01943 0.01324 0.0265 0.3886 0.8972
8.250 0.6730 0.02100 0.01436 0.0316 0.3120 0.9020
8.500 0.6564 0.02278 0.01564 0.0366 0.2273 0.9063
8.750 0.6401 0.02477 0.01700 0.0415 0.1307 0.9108
9.000 0.6363 0.02642 0.01829 0.0446 0.0866 0.9154
9.250 0.6433 0.02758 0.01937 0.0464 0.0734 0.9197
9.500 0.6489 0.02863 0.02041 0.0487 0.0660 0.9239
9.750 0.6591 0.02954 0.02135 0.0501 0.0616 0.9288
10.000 0.6679 0.03067 0.02247 0.0517 0.0576 0.9340
10.250 0.6812 0.03146 0.02331 0.0529 0.0538 0.9392
10.500 0.6940 0.03244 0.02423 0.0539 0.0509 0.9455
10.750 0.7132 0.03327 0.02511 0.0543 0.0489 0.9509
11.000 0.7356 0.03402 0.02593 0.0544 0.0469 0.9571
11.250 0.7627 0.03482 0.02674 0.0537 0.0451 0.9625
11.500 0.8018 0.03567 0.02747 0.0519 0.0431 0.9661
11.750 0.8380 0.03672 0.02866 0.0503 0.0418 0.9709
12.000 0.8701 0.03790 0.03001 0.0485 0.0403 0.9761
12.250 0.9067 0.03929 0.03154 0.0464 0.0392 0.9812
12.500 0.9428 0.04086 0.03325 0.0442 0.0384 0.9882
12.750 0.9748 0.04261 0.03513 0.0427 0.0378 1.0000
13.000 0.9973 0.04468 0.03741 0.0424 0.0377 1.0000
13.250 1.0160 0.04698 0.03992 0.0422 0.0375 1.0000
13.500 1.0245 0.04970 0.04293 0.0429 0.0376 1.0000
13.750 1.0182 0.05316 0.04683 0.0448 0.0382 1.0000
14.000 1.0076 0.05707 0.05114 0.0466 0.0390 1.0000
14.250 1.0023 0.05997 0.05424 0.0476 0.0385 1.0000
14.500 0.9834 0.06439 0.05901 0.0492 0.0393 1.0000
14.750 0.9663 0.06852 0.06338 0.0502 0.0396 1.0000
15.000 0.9476 0.07370 0.06879 0.0507 0.0409 1.0000
15.250 0.9308 0.07842 0.07369 0.0507 0.0414 1.0000
15.500 0.9144 0.08347 0.07890 0.0502 0.0419 1.0000
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