USA 33 AIRFOIL (usa33-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 33 AIRFOIL (usa33-il) Reynolds number: 1,000,000 Max Cl/Cd: 67.76 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa33-il-1000000-n5.txt Download as CSV file: xf-usa33-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 33 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -1.1400 0.03904 0.03574 -0.0764 1.0000 0.0294
-15.000 -1.1370 0.03418 0.03065 -0.0775 0.9979 0.0296
-14.750 -1.1185 0.03097 0.02728 -0.0789 0.9944 0.0298
-14.500 -1.1007 0.02897 0.02516 -0.0787 0.9890 0.0300
-14.250 -1.0815 0.02753 0.02361 -0.0784 0.9836 0.0302
-14.000 -1.0591 0.02635 0.02234 -0.0783 0.9780 0.0304
-13.750 -1.0391 0.02521 0.02111 -0.0777 0.9696 0.0306
-13.500 -1.0111 0.02411 0.01990 -0.0786 0.9604 0.0308
-13.250 -0.9699 0.02294 0.01862 -0.0821 0.9481 0.0311
-12.750 -0.8556 0.02054 0.01580 -0.0957 0.8812 0.0316
-12.250 -0.8213 0.01961 0.01446 -0.0919 0.8197 0.0318
-12.000 -0.8051 0.01903 0.01377 -0.0898 0.8073 0.0320
-11.750 -0.7873 0.01853 0.01318 -0.0879 0.7963 0.0322
-11.500 -0.7672 0.01811 0.01270 -0.0864 0.7876 0.0324
-11.250 -0.7468 0.01771 0.01223 -0.0850 0.7783 0.0326
-11.000 -0.7253 0.01736 0.01182 -0.0836 0.7702 0.0328
-10.750 -0.7035 0.01700 0.01140 -0.0824 0.7612 0.0330
-10.500 -0.6816 0.01668 0.01101 -0.0811 0.7523 0.0332
-10.250 -0.6589 0.01635 0.01062 -0.0799 0.7435 0.0334
-10.000 -0.6366 0.01605 0.01025 -0.0787 0.7327 0.0336
-9.750 -0.6136 0.01573 0.00986 -0.0775 0.7219 0.0339
-9.500 -0.5911 0.01544 0.00948 -0.0763 0.7094 0.0341
-9.250 -0.5680 0.01514 0.00910 -0.0752 0.6958 0.0344
-9.000 -0.5448 0.01487 0.00875 -0.0740 0.6828 0.0346
-8.750 -0.5216 0.01463 0.00841 -0.0729 0.6686 0.0349
-8.500 -0.4975 0.01439 0.00809 -0.0719 0.6549 0.0352
-8.250 -0.4738 0.01414 0.00775 -0.0708 0.6419 0.0354
-8.000 -0.4498 0.01392 0.00745 -0.0698 0.6285 0.0356
-7.750 -0.4262 0.01361 0.00707 -0.0688 0.6173 0.0359
-7.250 -0.3773 0.01315 0.00651 -0.0669 0.5964 0.0364
-6.750 -0.3273 0.01281 0.00607 -0.0653 0.5765 0.0370
-6.500 -0.3022 0.01266 0.00586 -0.0644 0.5666 0.0373
-6.250 -0.2768 0.01249 0.00564 -0.0636 0.5582 0.0376
-6.000 -0.2512 0.01232 0.00544 -0.0629 0.5506 0.0379
-5.750 -0.2258 0.01217 0.00523 -0.0621 0.5435 0.0383
-5.500 -0.1998 0.01200 0.00504 -0.0614 0.5391 0.0387
-5.250 -0.1735 0.01186 0.00487 -0.0608 0.5351 0.0391
-5.000 -0.1475 0.01172 0.00469 -0.0602 0.5297 0.0394
-4.750 -0.1218 0.01160 0.00452 -0.0594 0.5235 0.0397
-4.500 -0.0963 0.01139 0.00429 -0.0587 0.5188 0.0401
-4.250 -0.0701 0.01122 0.00412 -0.0580 0.5153 0.0405
-4.000 -0.0439 0.01108 0.00397 -0.0574 0.5111 0.0409
-3.750 -0.0178 0.01096 0.00384 -0.0568 0.5067 0.0413
-3.500 0.0082 0.01086 0.00372 -0.0561 0.5026 0.0417
-3.250 0.0341 0.01076 0.00360 -0.0554 0.4984 0.0422
-3.000 0.0607 0.01064 0.00348 -0.0548 0.4956 0.0426
-2.750 0.0871 0.01054 0.00338 -0.0542 0.4922 0.0432
-2.500 0.1134 0.01045 0.00328 -0.0536 0.4888 0.0437
-2.250 0.1396 0.01037 0.00319 -0.0530 0.4850 0.0441
-2.000 0.1649 0.01025 0.00305 -0.0522 0.4811 0.0446
-1.750 0.1906 0.01015 0.00296 -0.0515 0.4775 0.0452
-1.500 0.2168 0.01005 0.00288 -0.0508 0.4746 0.0457
-1.250 0.2429 0.00997 0.00280 -0.0502 0.4705 0.0463
-1.000 0.2685 0.00991 0.00273 -0.0495 0.4648 0.0470
-0.750 0.2936 0.00989 0.00267 -0.0486 0.4573 0.0477
-0.500 0.3194 0.00984 0.00262 -0.0479 0.4491 0.0483
-0.250 0.3439 0.00984 0.00257 -0.0470 0.4386 0.0490
0.000 0.3689 0.00978 0.00251 -0.0462 0.4291 0.0500
0.250 0.3930 0.00978 0.00247 -0.0452 0.4160 0.0509
0.500 0.4165 0.00983 0.00245 -0.0441 0.3983 0.0519
0.750 0.4386 0.00996 0.00247 -0.0427 0.3727 0.0528
1.000 0.4600 0.01013 0.00253 -0.0413 0.3487 0.0536
1.250 0.4827 0.01022 0.00256 -0.0401 0.3340 0.0550
1.500 0.5058 0.01028 0.00259 -0.0389 0.3238 0.0568
1.750 0.5293 0.01034 0.00262 -0.0378 0.3155 0.0588
2.000 0.5522 0.01039 0.00266 -0.0367 0.3077 0.0633
2.250 0.5740 0.01031 0.00269 -0.0353 0.3018 0.1012
2.500 0.5963 0.01039 0.00279 -0.0341 0.2928 0.1179
2.750 0.6199 0.01046 0.00287 -0.0330 0.2858 0.1284
3.000 0.6433 0.01055 0.00295 -0.0320 0.2784 0.1352
3.250 0.6660 0.01067 0.00305 -0.0309 0.2708 0.1422
3.500 0.6895 0.01076 0.00313 -0.0298 0.2639 0.1470
3.750 0.7114 0.01090 0.00325 -0.0285 0.2550 0.1522
4.000 0.7339 0.01102 0.00335 -0.0274 0.2460 0.1569
4.250 0.7544 0.01121 0.00348 -0.0259 0.2323 0.1600
4.500 0.7738 0.01142 0.00364 -0.0242 0.2179 0.1648
4.750 0.7889 0.01179 0.00388 -0.0217 0.1933 0.1691
5.000 0.8050 0.01210 0.00410 -0.0194 0.1768 0.1722
5.250 0.8194 0.01237 0.00431 -0.0168 0.1638 0.1750
5.500 0.8332 0.01258 0.00449 -0.0140 0.1550 0.1806
5.750 0.8483 0.01278 0.00467 -0.0115 0.1481 0.1854
6.000 0.8628 0.01304 0.00490 -0.0089 0.1407 0.1890
6.250 0.8784 0.01326 0.00512 -0.0065 0.1343 0.1941
6.500 0.8910 0.01361 0.00542 -0.0037 0.1236 0.1987
6.750 0.8865 0.01453 0.00610 0.0019 0.0820 0.2017
7.250 0.9016 0.01561 0.00711 0.0087 0.0568 0.2108
7.500 0.9158 0.01594 0.00746 0.0109 0.0552 0.2184
7.750 0.9298 0.01628 0.00783 0.0130 0.0541 0.2305
8.000 0.9421 0.01661 0.00826 0.0154 0.0531 0.2728
8.500 1.1123 0.01656 0.00986 -0.0104 0.0500 0.9884
8.750 1.1329 0.01707 0.01038 -0.0098 0.0497 0.9961
9.000 1.1624 0.01762 0.01092 -0.0111 0.0492 0.9985
9.250 1.1915 0.01819 0.01150 -0.0124 0.0487 0.9998
9.500 1.2047 0.01877 0.01210 -0.0106 0.0484 1.0000
9.750 1.2143 0.01940 0.01275 -0.0083 0.0481 1.0000
10.000 1.2241 0.02010 0.01346 -0.0062 0.0478 1.0000
10.250 1.2338 0.02087 0.01425 -0.0042 0.0475 1.0000
10.500 1.2437 0.02170 0.01511 -0.0024 0.0472 1.0000
10.750 1.2531 0.02262 0.01605 -0.0007 0.0469 1.0000
11.000 1.2623 0.02362 0.01708 0.0009 0.0466 1.0000
11.250 1.2716 0.02468 0.01816 0.0023 0.0463 1.0000
11.500 1.2803 0.02584 0.01935 0.0036 0.0459 1.0000
11.750 1.2878 0.02714 0.02068 0.0049 0.0456 1.0000
12.000 1.2952 0.02851 0.02209 0.0060 0.0454 1.0000
12.250 1.3014 0.03003 0.02366 0.0071 0.0451 1.0000
12.500 1.3094 0.03145 0.02512 0.0080 0.0450 1.0000
12.750 1.3172 0.03293 0.02664 0.0088 0.0449 1.0000
13.000 1.3239 0.03457 0.02833 0.0095 0.0448 1.0000
13.250 1.3306 0.03625 0.03005 0.0101 0.0447 1.0000
13.500 1.3368 0.03800 0.03186 0.0106 0.0446 1.0000
13.750 1.3421 0.03989 0.03379 0.0111 0.0445 1.0000
14.000 1.3464 0.04194 0.03590 0.0114 0.0444 1.0000
14.250 1.3508 0.04403 0.03804 0.0117 0.0443 1.0000
14.500 1.3541 0.04624 0.04031 0.0120 0.0442 1.0000
14.750 1.3574 0.04852 0.04264 0.0121 0.0441 1.0000
15.000 1.3594 0.05098 0.04516 0.0122 0.0439 1.0000
15.250 1.3610 0.05350 0.04774 0.0122 0.0439 1.0000
15.500 1.3609 0.05624 0.05055 0.0121 0.0438 1.0000
15.750 1.3615 0.05895 0.05332 0.0120 0.0437 1.0000
16.000 1.3616 0.06176 0.05619 0.0118 0.0436 1.0000
16.250 1.3600 0.06482 0.05931 0.0115 0.0434 1.0000
16.500 1.3597 0.06773 0.06228 0.0112 0.0433 1.0000
16.750 1.3569 0.07103 0.06566 0.0107 0.0432 1.0000
17.000 1.3536 0.07443 0.06913 0.0101 0.0432 1.0000
17.250 1.3509 0.07779 0.07256 0.0095 0.0430 1.0000
17.500 1.3466 0.08142 0.07626 0.0088 0.0430 1.0000
17.750 1.3429 0.08499 0.07990 0.0080 0.0429 1.0000
18.000 1.3389 0.08867 0.08365 0.0072 0.0428 1.0000
18.250 1.3331 0.09265 0.08770 0.0061 0.0427 1.0000
18.500 1.3282 0.09649 0.09161 0.0051 0.0427 1.0000
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Polar data table (+)
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