NACA 66(4)-221 (naca664221-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 66(4)-221 (naca664221-il) Reynolds number: 200,000 Max Cl/Cd: 29.56 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca664221-il-200000.txt Download as CSV file: xf-naca664221-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6801 0.06776 0.06237 -0.1265 0.9287 0.0482
-15.500 -0.6830 0.06428 0.05877 -0.1262 0.9229 0.0477
-15.250 -0.6937 0.06094 0.05525 -0.1252 0.9177 0.0471
-15.000 -0.7061 0.05783 0.05190 -0.1237 0.9131 0.0466
-14.750 -0.7181 0.05478 0.04861 -0.1218 0.9079 0.0461
-14.500 -0.7277 0.05200 0.04556 -0.1197 0.9031 0.0456
-14.250 -0.7353 0.04937 0.04262 -0.1174 0.8991 0.0452
-14.000 -0.7365 0.04715 0.04015 -0.1154 0.8954 0.0451
-13.750 -0.7321 0.04504 0.03779 -0.1140 0.8915 0.0449
-13.500 -0.7214 0.04318 0.03571 -0.1129 0.8879 0.0451
-13.250 -0.7068 0.04158 0.03390 -0.1120 0.8846 0.0453
-13.000 -0.6907 0.04026 0.03240 -0.1113 0.8818 0.0460
-12.750 -0.6744 0.03909 0.03105 -0.1105 0.8792 0.0468
-12.500 -0.6540 0.03791 0.02970 -0.1103 0.8764 0.0476
-12.250 -0.6305 0.03686 0.02847 -0.1103 0.8738 0.0482
-12.000 -0.6007 0.03589 0.02735 -0.1109 0.8716 0.0489
-11.750 -0.5548 0.03510 0.02667 -0.1131 0.8700 0.0503
-11.500 -0.5274 0.03451 0.02609 -0.1134 0.8679 0.0517
-11.250 -0.5017 0.03397 0.02551 -0.1134 0.8660 0.0533
-11.000 -0.4791 0.03347 0.02492 -0.1130 0.8641 0.0549
-10.750 -0.4561 0.03291 0.02443 -0.1127 0.8625 0.0574
-10.500 -0.4383 0.03241 0.02395 -0.1121 0.8607 0.0600
-10.250 -0.4202 0.03191 0.02342 -0.1116 0.8587 0.0623
-10.000 -0.4061 0.03121 0.02280 -0.1107 0.8567 0.0651
-9.750 -0.3931 0.03059 0.02220 -0.1096 0.8546 0.0685
-9.500 -0.3815 0.02993 0.02154 -0.1083 0.8526 0.0727
-9.250 -0.3723 0.02922 0.02087 -0.1068 0.8506 0.0781
-9.000 -0.3654 0.02841 0.02011 -0.1048 0.8486 0.0866
-8.750 -0.3608 0.02754 0.01933 -0.1024 0.8466 0.1024
-8.500 -0.3670 0.02627 0.01845 -0.0988 0.8447 0.1506
-8.250 -0.3844 0.02486 0.01760 -0.0936 0.8429 0.2411
-8.000 -0.4028 0.02387 0.01708 -0.0885 0.8404 0.3155
-7.750 -0.4228 0.02329 0.01688 -0.0826 0.8376 0.3762
-7.500 -0.4438 0.02310 0.01703 -0.0759 0.8348 0.4311
-7.250 -0.4557 0.02342 0.01783 -0.0696 0.8326 0.5004
-6.000 -0.6677 0.02714 0.02104 -0.0123 0.8263 0.4468
-5.750 -0.7122 0.02908 0.02249 -0.0009 0.8335 0.3728
-5.500 -0.7390 0.02861 0.02240 0.0076 0.8398 0.4399
-5.250 -0.7183 0.03003 0.02504 0.0107 0.8423 0.6430
-5.000 -0.1676 0.03817 0.03248 -0.0661 0.8254 0.6844
-4.750 -0.1236 0.03882 0.03304 -0.0685 0.8249 0.6873
-4.500 -0.0722 0.03946 0.03359 -0.0721 0.8246 0.6891
-4.250 -0.0605 0.04095 0.03509 -0.0695 0.8232 0.6930
-4.000 -0.4647 0.04184 0.03649 0.0003 0.8239 0.7234
-3.750 -0.3903 0.04539 0.04000 -0.0054 0.8221 0.7252
-3.500 -0.6915 0.03528 0.03001 0.0395 0.8515 0.7286
-3.250 -0.6642 0.03673 0.03139 0.0403 0.8482 0.7412
-3.000 -0.5729 0.04433 0.03911 0.0358 0.8476 0.7525
-2.750 -0.5181 0.04680 0.04151 0.0323 0.8459 0.7614
-2.500 -0.4409 0.04917 0.04377 0.0241 0.8450 0.7629
-2.250 -0.5129 0.04703 0.04165 0.0405 0.8347 0.7786
-2.000 -0.4572 0.04848 0.04303 0.0359 0.8312 0.7801
-1.750 -0.3942 0.04983 0.04430 0.0295 0.8288 0.7814
-1.500 -0.3299 0.05089 0.04528 0.0224 0.8268 0.7826
-1.250 -0.4272 0.04830 0.04270 0.0435 0.8154 0.7980
-1.000 -0.3812 0.04893 0.04326 0.0400 0.8109 0.7992
-0.750 -0.3219 0.04982 0.04408 0.0341 0.8080 0.8002
-0.500 -0.3083 0.04985 0.04409 0.0359 0.7981 0.8025
0.000 -0.1339 0.04926 0.04331 0.0163 0.7714 0.8036
0.250 -0.0694 0.04939 0.04340 0.0097 0.7695 0.8054
0.500 -0.0089 0.04945 0.04342 0.0038 0.7682 0.8077
0.750 -0.1741 0.04678 0.04074 0.0365 0.7527 0.8192
1.000 -0.1670 0.04658 0.04053 0.0394 0.7443 0.8211
1.250 -0.1524 0.04626 0.04020 0.0410 0.7382 0.8232
1.500 -0.1251 0.04586 0.03977 0.0406 0.7353 0.8248
1.750 -0.0926 0.04548 0.03935 0.0395 0.7334 0.8262
2.000 -0.0542 0.04522 0.03906 0.0374 0.7321 0.8276
2.250 -0.1053 0.04356 0.03736 0.0484 0.7177 0.8316
2.500 -0.0708 0.04308 0.03686 0.0467 0.7159 0.8323
2.750 -0.0327 0.04268 0.03643 0.0443 0.7146 0.8336
3.000 -0.0492 0.04215 0.03589 0.0493 0.7010 0.8350
3.250 -0.0114 0.04179 0.03552 0.0474 0.6990 0.8354
3.500 0.0281 0.04148 0.03522 0.0452 0.6977 0.8357
3.750 0.0207 0.04155 0.03531 0.0496 0.6848 0.8371
4.000 0.0574 0.04119 0.03497 0.0479 0.6826 0.8378
4.250 0.0958 0.04081 0.03461 0.0460 0.6811 0.8382
4.500 0.1369 0.04037 0.03420 0.0437 0.6800 0.8386
4.750 0.1316 0.04053 0.03437 0.0473 0.6663 0.8397
5.000 0.1700 0.04005 0.03393 0.0454 0.6647 0.8403
5.250 0.2102 0.03950 0.03342 0.0433 0.6635 0.8408
5.500 0.2113 0.03973 0.03367 0.0459 0.6504 0.8421
5.750 0.2497 0.03912 0.03312 0.0442 0.6487 0.8428
6.000 0.2905 0.03839 0.03244 0.0423 0.6474 0.8438
6.250 0.2954 0.03866 0.03275 0.0444 0.6348 0.8456
6.500 0.3361 0.03779 0.03194 0.0425 0.6330 0.8464
6.750 0.3786 0.03679 0.03101 0.0404 0.6316 0.8472
7.000 0.3875 0.03703 0.03129 0.0419 0.6195 0.8486
7.250 0.4292 0.03594 0.03028 0.0400 0.6175 0.8496
7.500 0.4732 0.03465 0.02908 0.0379 0.6161 0.8505
7.750 0.4890 0.03446 0.02895 0.0389 0.6038 0.8519
8.000 0.5507 0.03102 0.02559 0.0361 0.6006 0.8526
8.250 0.5696 0.03006 0.02470 0.0377 0.5861 0.8539
8.500 0.5908 0.02944 0.02415 0.0388 0.5716 0.8553
8.750 0.6218 0.02845 0.02322 0.0387 0.5568 0.8565
9.000 0.6720 0.02638 0.02114 0.0368 0.5357 0.8576
9.250 0.7157 0.02483 0.01939 0.0357 0.4910 0.8588
9.500 0.7328 0.02479 0.01901 0.0372 0.4338 0.8606
9.750 0.7313 0.02584 0.01976 0.0405 0.3819 0.8632
10.000 0.7249 0.02729 0.02090 0.0439 0.3302 0.8660
10.250 0.7156 0.02908 0.02235 0.0472 0.2731 0.8685
10.500 0.7048 0.03116 0.02401 0.0503 0.2086 0.8707
10.750 0.6908 0.03335 0.02574 0.0539 0.1394 0.8728
11.000 0.6824 0.03545 0.02746 0.0569 0.0935 0.8750
11.250 0.6833 0.03708 0.02896 0.0588 0.0783 0.8774
11.500 0.6881 0.03855 0.03039 0.0603 0.0691 0.8800
11.750 0.6963 0.03985 0.03172 0.0613 0.0636 0.8827
12.000 0.7029 0.04135 0.03316 0.0623 0.0593 0.8855
12.250 0.7149 0.04251 0.03437 0.0628 0.0561 0.8881
12.500 0.7219 0.04379 0.03561 0.0641 0.0530 0.8907
12.750 0.7336 0.04482 0.03672 0.0650 0.0508 0.8937
13.000 0.7460 0.04589 0.03780 0.0657 0.0483 0.8969
13.250 0.7618 0.04680 0.03861 0.0662 0.0463 0.9002
13.500 0.7808 0.04760 0.03949 0.0664 0.0452 0.9036
13.750 0.7986 0.04830 0.04026 0.0669 0.0440 0.9070
14.000 0.8170 0.04901 0.04101 0.0675 0.0424 0.9111
14.250 0.8414 0.04950 0.04143 0.0675 0.0411 0.9154
14.500 0.8701 0.05009 0.04204 0.0672 0.0400 0.9197
14.750 0.8858 0.05111 0.04325 0.0678 0.0392 0.9244
15.000 0.9034 0.05224 0.04452 0.0681 0.0384 0.9298
15.250 0.9215 0.05342 0.04582 0.0682 0.0375 0.9354
15.500 0.9420 0.05462 0.04714 0.0681 0.0370 0.9414
15.750 0.9627 0.05597 0.04860 0.0678 0.0366 0.9483
16.000 0.9836 0.05764 0.05041 0.0672 0.0362 0.9554
16.250 1.0054 0.05971 0.05265 0.0659 0.0359 0.9629
16.500 1.0324 0.06231 0.05539 0.0640 0.0355 0.9701
16.750 1.0423 0.06533 0.05868 0.0626 0.0355 0.9811
17.000 1.0339 0.06836 0.06199 0.0629 0.0358 1.0000
17.250 1.0265 0.07205 0.06595 0.0628 0.0359 1.0000
17.500 0.9946 0.07752 0.07186 0.0630 0.0363 1.0000
17.750 0.9546 0.08466 0.07947 0.0623 0.0369 1.0000
18.000 0.9195 0.09217 0.08735 0.0606 0.0378 1.0000
18.250 0.8909 0.09947 0.09492 0.0580 0.0384 1.0000
18.500 0.8609 0.10746 0.10314 0.0544 0.0389 1.0000
18.750 0.8347 0.11545 0.11131 0.0504 0.0395 1.0000
19.000 0.8171 0.12267 0.11865 0.0465 0.0400 1.0000
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