USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.89 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa32-il-1000000.txt Download as CSV file: xf-usa32-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: USA 32 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
------ -------- --------- --------- -------- -------- --------
-11.500 0.2766 0.09001 0.08767 -0.1722 0.9017 0.0200
-11.250 0.2891 0.08753 0.08516 -0.1742 0.8975 0.0203
-11.000 0.2872 0.08315 0.08076 -0.1776 0.8917 0.0224
-10.750 0.3647 0.06515 0.06276 -0.1821 0.8735 0.0229
-10.500 0.3787 0.06336 0.06095 -0.1829 0.8694 0.0232
-10.250 0.3175 0.07459 0.07214 -0.1831 0.8784 0.0229
-10.000 0.3294 0.07267 0.07021 -0.1841 0.8739 0.0231
-9.750 0.3457 0.07083 0.06834 -0.1859 0.8697 0.0234
-9.500 0.3656 0.06848 0.06594 -0.1895 0.8657 0.0237
-9.250 0.3723 0.06657 0.06406 -0.1898 0.8614 0.0247
-9.000 0.3553 0.05862 0.05609 -0.1963 0.8547 0.0266
-8.750 0.3668 0.05657 0.05400 -0.1978 0.8496 0.0268
-8.500 0.3766 0.05601 0.05346 -0.1966 0.8443 0.0270
-8.250 0.3783 0.05402 0.05146 -0.1968 0.8372 0.0272
-8.000 0.3811 0.05226 0.04966 -0.1969 0.8306 0.0275
-7.750 0.3751 0.05083 0.04824 -0.1943 0.8231 0.0277
-7.500 0.2853 0.03407 0.03116 -0.1981 0.8128 0.0307
-7.250 0.2371 0.02605 0.02263 -0.1924 0.8035 0.0311
-7.000 0.2504 0.02546 0.02211 -0.1898 0.7945 0.0315
-6.750 0.2546 0.02446 0.02102 -0.1858 0.7821 0.0317
-6.500 0.2566 0.02375 0.02022 -0.1810 0.7643 0.0320
-6.250 0.2424 0.02304 0.01932 -0.1727 0.7319 0.0321
-6.000 0.2152 0.02277 0.01872 -0.1615 0.6754 0.0322
-5.750 0.2101 0.02228 0.01805 -0.1550 0.6539 0.0325
-5.500 0.2132 0.02139 0.01698 -0.1504 0.6433 0.0329
-5.250 0.2198 0.02043 0.01583 -0.1465 0.6361 0.0335
-5.000 0.2348 0.02147 0.01649 -0.1432 0.6295 0.0356
-4.750 0.2296 0.01817 0.01290 -0.1375 0.6257 0.0364
-4.500 0.2489 0.01766 0.01239 -0.1356 0.6214 0.0349
-4.250 0.2643 0.01745 0.01196 -0.1328 0.6172 0.0354
-3.750 0.2892 0.01440 0.00835 -0.1260 0.6103 0.0305
-3.500 0.3085 0.01379 0.00767 -0.1241 0.6075 0.0305
-3.250 0.3290 0.01350 0.00729 -0.1225 0.6046 0.0306
-3.000 0.3493 0.01331 0.00699 -0.1207 0.6012 0.0308
-2.750 0.3685 0.01257 0.00619 -0.1189 0.5981 0.0312
-2.500 0.3894 0.01221 0.00578 -0.1174 0.5944 0.0315
-2.250 0.4116 0.01197 0.00553 -0.1161 0.5919 0.0319
-2.000 0.4338 0.01180 0.00538 -0.1148 0.5896 0.0327
-1.750 0.4554 0.01160 0.00516 -0.1134 0.5865 0.0328
-1.500 0.4771 0.01147 0.00501 -0.1120 0.5836 0.0332
-1.250 0.4977 0.01136 0.00487 -0.1104 0.5802 0.0335
-1.000 0.5190 0.01129 0.00476 -0.1090 0.5766 0.0338
-0.750 0.5415 0.01119 0.00464 -0.1078 0.5736 0.0341
-0.500 0.5636 0.01109 0.00455 -0.1065 0.5710 0.0346
-0.250 0.5857 0.01100 0.00446 -0.1052 0.5677 0.0349
0.000 0.6075 0.01096 0.00440 -0.1039 0.5640 0.0352
0.250 0.6278 0.01098 0.00438 -0.1023 0.5599 0.0356
0.500 0.6488 0.01089 0.00425 -0.1009 0.5557 0.0365
0.750 0.6713 0.01079 0.00417 -0.0997 0.5526 0.0381
1.000 0.6933 0.01077 0.00416 -0.0985 0.5485 0.0386
1.250 0.7141 0.01079 0.00416 -0.0971 0.5439 0.0393
1.500 0.7332 0.01087 0.00419 -0.0953 0.5389 0.0405
1.750 0.7554 0.01087 0.00420 -0.0942 0.5346 0.0416
2.000 0.7758 0.01090 0.00423 -0.0927 0.5289 0.0441
2.250 0.7936 0.01100 0.00431 -0.0907 0.5224 0.0480
2.500 0.8120 0.01075 0.00444 -0.0890 0.5162 0.1894
2.750 0.8295 0.01089 0.00460 -0.0871 0.5070 0.2108
3.000 0.8478 0.01107 0.00476 -0.0853 0.4989 0.2210
3.250 0.8642 0.01128 0.00495 -0.0832 0.4886 0.2292
3.500 0.8827 0.01148 0.00512 -0.0816 0.4782 0.2345
3.750 0.8988 0.01176 0.00534 -0.0795 0.4680 0.2392
4.000 0.9146 0.01204 0.00559 -0.0774 0.4564 0.2463
4.250 0.9323 0.01230 0.00583 -0.0757 0.4462 0.2523
4.500 0.9482 0.01263 0.00609 -0.0737 0.4362 0.2569
4.750 0.9674 0.01286 0.00633 -0.0724 0.4283 0.2644
5.000 0.9836 0.01321 0.00664 -0.0705 0.4204 0.2721
5.250 1.0038 0.01343 0.00688 -0.0693 0.4139 0.2806
5.500 1.0217 0.01375 0.00718 -0.0679 0.4064 0.2891
5.750 1.0404 0.01405 0.00747 -0.0665 0.3996 0.2965
6.000 1.0600 0.01432 0.00776 -0.0654 0.3942 0.3042
6.250 1.0773 0.01469 0.00810 -0.0639 0.3881 0.3112
6.500 1.0970 0.01498 0.00841 -0.0629 0.3836 0.3193
6.750 1.1180 0.01524 0.00868 -0.0620 0.3793 0.3264
7.000 1.1371 0.01557 0.00901 -0.0609 0.3745 0.3322
7.250 1.1542 0.01599 0.00943 -0.0596 0.3698 0.3386
7.500 1.1743 0.01630 0.00975 -0.0587 0.3663 0.3444
7.750 1.1953 0.01658 0.01006 -0.0580 0.3623 0.3500
8.000 1.2148 0.01693 0.01043 -0.0571 0.3585 0.3561
8.250 1.2318 0.01739 0.01087 -0.0559 0.3542 0.3606
8.500 1.2506 0.01781 0.01131 -0.0549 0.3503 0.3654
8.750 1.2718 0.01812 0.01166 -0.0544 0.3468 0.3702
9.000 1.2918 0.01849 0.01205 -0.0538 0.3435 0.3750
9.250 1.3090 0.01900 0.01256 -0.0527 0.3384 0.3793
9.500 1.3257 0.01957 0.01314 -0.0517 0.3344 0.3842
9.750 1.3474 0.01990 0.01352 -0.0514 0.3317 0.3894
10.000 1.3673 0.02033 0.01397 -0.0509 0.3275 0.3938
10.250 1.3863 0.02085 0.01453 -0.0504 0.3233 0.4008
10.500 1.4007 0.02160 0.01527 -0.0492 0.3182 0.4068
10.750 1.4229 0.02200 0.01574 -0.0493 0.3161 0.4154
11.000 1.5644 0.02280 0.01765 -0.0762 0.3038 0.9960
11.250 1.6222 0.02371 0.01858 -0.0843 0.2964 1.0000
11.500 1.6326 0.02454 0.01940 -0.0824 0.2898 1.0000
11.750 1.6437 0.02535 0.02021 -0.0806 0.2845 1.0000
12.000 1.6573 0.02603 0.02091 -0.0792 0.2785 1.0000
12.250 1.6670 0.02697 0.02186 -0.0774 0.2734 1.0000
12.500 1.6770 0.02791 0.02279 -0.0757 0.2652 1.0000
12.750 1.6813 0.02925 0.02408 -0.0734 0.2548 1.0000
13.000 1.6903 0.03030 0.02514 -0.0717 0.2456 1.0000
13.250 1.6920 0.03188 0.02667 -0.0693 0.2326 1.0000
13.500 1.6892 0.03382 0.02855 -0.0666 0.2155 1.0000
13.750 1.6827 0.03614 0.03079 -0.0637 0.1985 1.0000
14.000 1.6765 0.03854 0.03313 -0.0610 0.1847 1.0000
14.250 1.6701 0.04106 0.03561 -0.0586 0.1732 1.0000
14.500 1.6667 0.04343 0.03797 -0.0567 0.1651 1.0000
14.750 1.6671 0.04557 0.04013 -0.0551 0.1596 1.0000
15.000 1.6631 0.04814 0.04271 -0.0534 0.1524 1.0000
15.250 1.6662 0.05011 0.04472 -0.0523 0.1485 1.0000
15.500 1.6650 0.05250 0.04713 -0.0510 0.1435 1.0000
15.750 1.6629 0.05502 0.04967 -0.0498 0.1379 1.0000
16.000 1.6627 0.05741 0.05209 -0.0487 0.1323 1.0000
16.250 1.6561 0.06044 0.05512 -0.0475 0.1259 1.0000
16.500 1.6559 0.06282 0.05754 -0.0465 0.1201 1.0000
16.750 1.6468 0.06620 0.06091 -0.0454 0.1126 1.0000
17.000 1.6353 0.06990 0.06459 -0.0443 0.1029 1.0000
17.250 1.6203 0.07405 0.06873 -0.0433 0.0931 1.0000
17.500 1.6097 0.07778 0.07247 -0.0425 0.0863 1.0000
17.750 1.5955 0.08204 0.07673 -0.0418 0.0798 1.0000
18.000 1.5893 0.08545 0.08019 -0.0415 0.0764 1.0000
18.250 1.5749 0.08989 0.08465 -0.0411 0.0708 1.0000
18.500 1.5664 0.09364 0.08843 -0.0409 0.0657 1.0000
18.750 1.5546 0.09786 0.09268 -0.0408 0.0610 1.0000
19.000 1.5378 0.10281 0.09763 -0.0409 0.0532 1.0000
19.250 1.5250 0.10733 0.10216 -0.0412 0.0472 1.0000
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