NACA 66(4)-221 (naca664221-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 66(4)-221 (naca664221-il) Reynolds number: 200,000 Max Cl/Cd: 30.51 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca664221-il-200000-n5.txt Download as CSV file: xf-naca664221-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 66(4)-221
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.250 -0.6573 0.10936 0.10453 -0.0927 0.9339 0.0243
-19.000 -0.6943 0.09853 0.09334 -0.0995 0.9283 0.0242
-18.750 -0.7082 0.09238 0.08699 -0.1031 0.9208 0.0243
-18.250 -0.7402 0.08067 0.07477 -0.1089 0.9075 0.0243
-18.000 -0.7460 0.07670 0.07062 -0.1105 0.9010 0.0244
-17.750 -0.7503 0.07310 0.06686 -0.1117 0.8952 0.0245
-17.500 -0.7537 0.06980 0.06341 -0.1126 0.8893 0.0247
-17.250 -0.7569 0.06660 0.06001 -0.1132 0.8838 0.0247
-17.000 -0.7569 0.06387 0.05712 -0.1137 0.8790 0.0249
-16.750 -0.7562 0.06134 0.05445 -0.1139 0.8739 0.0251
-16.500 -0.7544 0.05893 0.05188 -0.1139 0.8690 0.0253
-16.250 -0.7509 0.05675 0.04954 -0.1138 0.8647 0.0255
-16.000 -0.7465 0.05473 0.04735 -0.1136 0.8610 0.0257
-15.750 -0.7402 0.05286 0.04533 -0.1133 0.8569 0.0260
-15.500 -0.7332 0.05110 0.04343 -0.1130 0.8530 0.0264
-15.250 -0.7248 0.04946 0.04163 -0.1126 0.8493 0.0268
-15.000 -0.7151 0.04796 0.03996 -0.1122 0.8460 0.0272
-14.750 -0.7044 0.04655 0.03836 -0.1117 0.8432 0.0276
-14.500 -0.6928 0.04523 0.03687 -0.1113 0.8400 0.0280
-14.250 -0.6767 0.04416 0.03582 -0.1111 0.8368 0.0285
-14.000 -0.6621 0.04311 0.03473 -0.1108 0.8337 0.0289
-13.750 -0.6472 0.04210 0.03367 -0.1104 0.8309 0.0293
-13.500 -0.6330 0.04109 0.03259 -0.1099 0.8282 0.0299
-13.250 -0.6184 0.04013 0.03154 -0.1094 0.8258 0.0304
-13.000 -0.6034 0.03920 0.03052 -0.1089 0.8236 0.0310
-12.750 -0.5886 0.03828 0.02954 -0.1084 0.8211 0.0316
-12.500 -0.5738 0.03739 0.02856 -0.1078 0.8184 0.0322
-12.250 -0.5608 0.03642 0.02758 -0.1071 0.8159 0.0329
-12.000 -0.5477 0.03550 0.02665 -0.1063 0.8135 0.0336
-11.750 -0.5349 0.03459 0.02570 -0.1055 0.8111 0.0344
-11.500 -0.5213 0.03376 0.02480 -0.1047 0.8090 0.0356
-11.250 -0.5079 0.03293 0.02388 -0.1039 0.8069 0.0368
-11.000 -0.4957 0.03205 0.02296 -0.1029 0.8050 0.0379
-10.750 -0.4835 0.03120 0.02211 -0.1019 0.8028 0.0394
-10.500 -0.4702 0.03043 0.02131 -0.1010 0.8007 0.0408
-10.250 -0.4568 0.02969 0.02052 -0.1000 0.7986 0.0422
-10.000 -0.4443 0.02890 0.01973 -0.0989 0.7966 0.0440
-9.750 -0.4309 0.02820 0.01899 -0.0979 0.7946 0.0463
-9.500 -0.4166 0.02755 0.01829 -0.0969 0.7929 0.0490
-9.250 -0.4034 0.02685 0.01760 -0.0957 0.7912 0.0525
-9.000 -0.3897 0.02620 0.01694 -0.0945 0.7897 0.0576
-8.750 -0.3763 0.02555 0.01630 -0.0933 0.7883 0.0654
-8.500 -0.3638 0.02488 0.01567 -0.0920 0.7870 0.0776
-8.250 -0.3538 0.02413 0.01507 -0.0903 0.7855 0.0992
-8.000 -0.3471 0.02329 0.01446 -0.0882 0.7837 0.1366
-7.750 -0.3438 0.02235 0.01381 -0.0857 0.7819 0.1866
-7.500 -0.3418 0.02143 0.01316 -0.0829 0.7800 0.2354
-7.250 -0.3434 0.02046 0.01246 -0.0794 0.7781 0.2879
-7.000 -0.3458 0.01953 0.01179 -0.0757 0.7762 0.3379
-6.750 -0.3517 0.01858 0.01111 -0.0712 0.7742 0.3911
-6.500 -0.3560 0.01775 0.01060 -0.0666 0.7723 0.4493
-6.250 -0.3346 0.01799 0.01132 -0.0649 0.7712 0.5264
-6.000 -0.2363 0.02228 0.01592 -0.0721 0.7715 0.5968
-5.750 -0.2361 0.02181 0.01542 -0.0683 0.7701 0.6232
-5.500 -0.2277 0.02182 0.01537 -0.0654 0.7690 0.6407
-5.250 -0.2226 0.02163 0.01512 -0.0621 0.7677 0.6544
-5.000 -0.2184 0.02158 0.01507 -0.0586 0.7659 0.6654
-4.750 -0.1984 0.02194 0.01540 -0.0573 0.7645 0.6708
-4.500 -0.2430 0.02122 0.01470 -0.0459 0.7612 0.6861
-4.250 -0.1994 0.02196 0.01539 -0.0484 0.7605 0.6873
-4.000 -0.1580 0.02261 0.01598 -0.0505 0.7597 0.6883
-3.500 -0.1598 0.02243 0.01574 -0.0414 0.7560 0.7040
-3.250 -0.1223 0.02290 0.01616 -0.0430 0.7551 0.7051
-3.000 -0.0891 0.02323 0.01645 -0.0439 0.7542 0.7062
-2.750 -0.0598 0.02347 0.01665 -0.0444 0.7534 0.7075
-2.250 -0.0663 0.02250 0.01556 -0.0350 0.7508 0.7218
-2.000 -0.0361 0.02270 0.01574 -0.0357 0.7502 0.7227
-1.750 -0.0147 0.02314 0.01619 -0.0347 0.7488 0.7240
-1.500 -0.0234 0.02411 0.01725 -0.0286 0.7438 0.7267
-1.250 -0.0250 0.02461 0.01777 -0.0239 0.7405 0.7301
-0.750 -0.0288 0.02381 0.01685 -0.0152 0.7355 0.7405
-0.500 -0.0026 0.02383 0.01686 -0.0152 0.7345 0.7414
-0.250 0.0250 0.02380 0.01681 -0.0154 0.7336 0.7424
0.000 0.0525 0.02377 0.01677 -0.0157 0.7329 0.7435
0.250 0.0800 0.02371 0.01670 -0.0160 0.7322 0.7446
1.250 0.0105 0.02633 0.01931 0.0108 0.7032 0.7567
1.500 0.0373 0.02613 0.01907 0.0104 0.7016 0.7579
1.750 0.0665 0.02593 0.01886 0.0097 0.7003 0.7588
2.000 0.0966 0.02576 0.01869 0.0090 0.6992 0.7594
2.250 0.1278 0.02556 0.01850 0.0082 0.6983 0.7600
2.500 0.1601 0.02532 0.01828 0.0072 0.6976 0.7606
2.750 0.1924 0.02508 0.01806 0.0062 0.6970 0.7612
3.250 0.1985 0.02642 0.01946 0.0126 0.6822 0.7638
3.500 0.2306 0.02618 0.01924 0.0117 0.6812 0.7648
3.750 0.2638 0.02587 0.01896 0.0107 0.6804 0.7659
4.250 0.2825 0.02675 0.01990 0.0150 0.6659 0.7686
4.500 0.3158 0.02636 0.01955 0.0140 0.6647 0.7696
4.750 0.3505 0.02589 0.01912 0.0128 0.6637 0.7706
5.750 0.4085 0.02690 0.02027 0.0184 0.6345 0.7762
6.000 0.4418 0.02634 0.01976 0.0175 0.6323 0.7773
6.500 0.4765 0.02650 0.02006 0.0199 0.6164 0.7794
7.500 0.5486 0.02669 0.02052 0.0243 0.5708 0.7847
7.750 0.6127 0.02362 0.01729 0.0212 0.5330 0.7857
8.000 0.6637 0.02175 0.01497 0.0193 0.4670 0.7867
8.250 0.6722 0.02235 0.01532 0.0217 0.4226 0.7885
8.500 0.6740 0.02333 0.01608 0.0247 0.3807 0.7903
8.750 0.6734 0.02453 0.01704 0.0278 0.3404 0.7923
9.000 0.6734 0.02579 0.01809 0.0305 0.2997 0.7942
9.250 0.6738 0.02713 0.01920 0.0331 0.2585 0.7961
9.750 0.6769 0.02984 0.02149 0.0378 0.1769 0.7993
10.000 0.6800 0.03121 0.02264 0.0398 0.1370 0.8009
10.250 0.6844 0.03257 0.02380 0.0416 0.1013 0.8027
10.500 0.6913 0.03384 0.02492 0.0430 0.0780 0.8046
10.750 0.7010 0.03497 0.02599 0.0442 0.0633 0.8066
11.000 0.7116 0.03608 0.02706 0.0452 0.0540 0.8087
11.250 0.7229 0.03717 0.02815 0.0460 0.0481 0.8108
11.500 0.7344 0.03829 0.02928 0.0468 0.0434 0.8131
11.750 0.7456 0.03947 0.03046 0.0476 0.0407 0.8153
12.000 0.7569 0.04059 0.03165 0.0484 0.0380 0.8173
12.250 0.7673 0.04180 0.03293 0.0492 0.0364 0.8193
12.500 0.7766 0.04313 0.03431 0.0501 0.0345 0.8216
12.750 0.7870 0.04440 0.03567 0.0508 0.0331 0.8243
13.000 0.7964 0.04580 0.03713 0.0514 0.0315 0.8270
13.250 0.8046 0.04734 0.03870 0.0521 0.0304 0.8300
13.500 0.8142 0.04881 0.04025 0.0526 0.0297 0.8330
13.750 0.8235 0.05028 0.04181 0.0531 0.0290 0.8356
14.000 0.8315 0.05184 0.04345 0.0538 0.0279 0.8382
14.250 0.8394 0.05346 0.04513 0.0543 0.0272 0.8410
14.500 0.8469 0.05515 0.04688 0.0548 0.0267 0.8441
14.750 0.8556 0.05682 0.04860 0.0551 0.0262 0.8474
15.000 0.8652 0.05847 0.05035 0.0553 0.0255 0.8508
15.250 0.8747 0.06012 0.05210 0.0555 0.0250 0.8540
15.500 0.8837 0.06178 0.05385 0.0558 0.0245 0.8572
15.750 0.8923 0.06352 0.05568 0.0559 0.0240 0.8608
16.000 0.9013 0.06529 0.05752 0.0559 0.0235 0.8648
16.250 0.9102 0.06713 0.05940 0.0558 0.0231 0.8689
16.500 0.9183 0.06902 0.06133 0.0557 0.0226 0.8728
16.750 0.9269 0.07091 0.06338 0.0557 0.0223 0.8771
17.000 0.9356 0.07281 0.06540 0.0556 0.0221 0.8820
17.250 0.9423 0.07502 0.06776 0.0553 0.0216 0.8871
17.500 0.9487 0.07722 0.07010 0.0551 0.0213 0.8923
17.750 0.9541 0.07956 0.07258 0.0548 0.0210 0.8984
18.250 0.9635 0.08456 0.07788 0.0538 0.0205 0.9128
18.500 0.9667 0.08735 0.08081 0.0531 0.0203 0.9218
18.750 0.9697 0.09032 0.08393 0.0520 0.0201 0.9324
19.000 0.9733 0.09354 0.08730 0.0503 0.0199 0.9446
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