USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 500,000 Max Cl/Cd: 59.6 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa32-il-500000-n5.txt Download as CSV file: xf-usa32-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 0.2288 0.10357 0.10045 -0.1632 0.9030 0.0150
-12.500 0.2421 0.10027 0.09712 -0.1663 0.8998 0.0149
-12.250 0.2418 0.09528 0.09210 -0.1687 0.8953 0.0157
-12.000 0.2608 0.09408 0.09090 -0.1704 0.8915 0.0160
-11.750 0.2733 0.09081 0.08759 -0.1734 0.8880 0.0160
-11.500 0.2942 0.08889 0.08563 -0.1766 0.8849 0.0167
-11.250 0.3053 0.08621 0.08294 -0.1786 0.8809 0.0172
-11.000 0.3128 0.08335 0.08007 -0.1802 0.8759 0.0176
-10.750 0.3218 0.08016 0.07685 -0.1825 0.8710 0.0179
-10.500 0.3247 0.07537 0.07201 -0.1862 0.8667 0.0188
-10.250 0.3406 0.07498 0.07163 -0.1861 0.8623 0.0193
-10.000 0.3466 0.07265 0.06930 -0.1868 0.8573 0.0195
-9.750 0.3558 0.07045 0.06708 -0.1881 0.8524 0.0200
-9.500 0.3637 0.06766 0.06425 -0.1899 0.8478 0.0202
-9.250 0.3632 0.06515 0.06177 -0.1899 0.8427 0.0207
-9.000 0.3338 0.05797 0.05457 -0.1918 0.8351 0.0220
-8.750 0.3351 0.05572 0.05231 -0.1924 0.8295 0.0221
-8.500 0.3309 0.05417 0.05079 -0.1910 0.8233 0.0223
-8.250 0.3218 0.05225 0.04886 -0.1891 0.8159 0.0224
-8.000 0.3169 0.05105 0.04766 -0.1865 0.8082 0.0226
-7.750 0.3137 0.04938 0.04598 -0.1846 0.7992 0.0229
-7.250 0.1681 0.02513 0.02079 -0.1768 0.7761 0.0242
-7.000 0.1631 0.02299 0.01832 -0.1718 0.7638 0.0246
-6.750 0.1593 0.02146 0.01646 -0.1661 0.7483 0.0250
-6.500 0.1581 0.02040 0.01505 -0.1606 0.7237 0.0254
-6.250 0.1516 0.01979 0.01404 -0.1536 0.6871 0.0256
-5.750 0.1533 0.01866 0.01240 -0.1429 0.6493 0.0259
-5.500 0.1634 0.01812 0.01171 -0.1394 0.6397 0.0261
-5.250 0.1758 0.01769 0.01113 -0.1363 0.6312 0.0263
-5.000 0.1910 0.01729 0.01061 -0.1338 0.6242 0.0266
-4.750 0.2083 0.01687 0.01008 -0.1316 0.6190 0.0268
-4.500 0.2260 0.01651 0.00961 -0.1295 0.6144 0.0271
-4.250 0.2446 0.01622 0.00921 -0.1276 0.6102 0.0275
-4.000 0.2643 0.01587 0.00876 -0.1259 0.6067 0.0279
-3.750 0.2846 0.01557 0.00837 -0.1242 0.6031 0.0283
-3.500 0.3050 0.01527 0.00797 -0.1226 0.5995 0.0287
-3.250 0.3259 0.01501 0.00760 -0.1211 0.5961 0.0290
-3.000 0.3467 0.01481 0.00729 -0.1196 0.5923 0.0292
-2.750 0.3686 0.01461 0.00702 -0.1182 0.5893 0.0294
-2.500 0.3902 0.01442 0.00678 -0.1168 0.5862 0.0297
-2.250 0.4117 0.01427 0.00658 -0.1154 0.5829 0.0299
-2.000 0.4327 0.01404 0.00633 -0.1140 0.5795 0.0300
-1.750 0.4538 0.01381 0.00609 -0.1126 0.5764 0.0306
-1.500 0.4752 0.01369 0.00594 -0.1112 0.5732 0.0309
-1.250 0.4970 0.01359 0.00582 -0.1099 0.5700 0.0315
-1.000 0.5185 0.01349 0.00572 -0.1086 0.5662 0.0318
-0.750 0.5402 0.01340 0.00562 -0.1073 0.5626 0.0323
-0.500 0.5612 0.01334 0.00554 -0.1059 0.5587 0.0328
-0.250 0.5822 0.01331 0.00548 -0.1044 0.5550 0.0332
0.000 0.6038 0.01328 0.00543 -0.1031 0.5515 0.0336
0.250 0.6257 0.01324 0.00539 -0.1019 0.5474 0.0341
0.500 0.6469 0.01324 0.00537 -0.1006 0.5428 0.0346
0.750 0.6662 0.01326 0.00536 -0.0989 0.5373 0.0349
1.000 0.6868 0.01326 0.00534 -0.0975 0.5324 0.0358
1.250 0.7073 0.01328 0.00536 -0.0961 0.5264 0.0370
1.500 0.7263 0.01336 0.00541 -0.0944 0.5205 0.0378
1.750 0.7460 0.01343 0.00546 -0.0929 0.5143 0.0394
2.000 0.7650 0.01353 0.00554 -0.0912 0.5069 0.0407
2.250 0.7817 0.01368 0.00565 -0.0892 0.4995 0.0430
2.500 0.7995 0.01379 0.00577 -0.0873 0.4897 0.0512
2.750 0.8150 0.01372 0.00601 -0.0852 0.4813 0.1777
3.000 0.8308 0.01395 0.00623 -0.0831 0.4713 0.1976
3.250 0.8465 0.01421 0.00649 -0.0810 0.4619 0.2112
3.500 0.8625 0.01450 0.00672 -0.0790 0.4527 0.2166
3.750 0.8797 0.01476 0.00698 -0.0773 0.4448 0.2279
4.000 0.8958 0.01507 0.00726 -0.0753 0.4368 0.2333
4.250 0.9130 0.01536 0.00752 -0.0736 0.4301 0.2395
4.500 0.9311 0.01563 0.00780 -0.0721 0.4234 0.2476
4.750 0.9476 0.01597 0.00811 -0.0704 0.4172 0.2539
5.000 0.9655 0.01627 0.00843 -0.0689 0.4108 0.2637
5.250 0.9835 0.01658 0.00874 -0.0675 0.4054 0.2719
5.500 0.9992 0.01698 0.00910 -0.0657 0.3991 0.2767
5.750 1.0181 0.01728 0.00943 -0.0645 0.3931 0.2835
6.000 1.0353 0.01765 0.00979 -0.0630 0.3870 0.2898
6.250 1.0509 0.01809 0.01021 -0.0613 0.3817 0.2956
6.500 1.0701 0.01840 0.01055 -0.0603 0.3779 0.3022
6.750 1.0890 0.01874 0.01091 -0.0592 0.3732 0.3095
7.000 1.1068 0.01913 0.01131 -0.0579 0.3689 0.3168
7.250 1.1209 0.01969 0.01185 -0.0562 0.3631 0.3234
7.500 1.1403 0.02003 0.01222 -0.0553 0.3602 0.3298
7.750 1.1593 0.02040 0.01262 -0.0543 0.3568 0.3347
8.000 1.1775 0.02080 0.01306 -0.0533 0.3534 0.3405
8.250 1.1938 0.02131 0.01357 -0.0520 0.3494 0.3458
8.500 1.2096 0.02185 0.01411 -0.0507 0.3461 0.3506
8.750 1.2278 0.02229 0.01459 -0.0498 0.3432 0.3554
9.000 1.2462 0.02273 0.01508 -0.0490 0.3398 0.3604
9.250 1.2639 0.02322 0.01560 -0.0481 0.3366 0.3647
9.500 1.2795 0.02382 0.01623 -0.0469 0.3328 0.3696
9.750 1.2929 0.02454 0.01696 -0.0456 0.3282 0.3751
10.000 1.3108 0.02506 0.01752 -0.0448 0.3252 0.3800
10.250 1.3277 0.02565 0.01817 -0.0440 0.3210 0.3850
10.500 1.3422 0.02639 0.01893 -0.0429 0.3162 0.3897
10.750 1.3565 0.02714 0.01971 -0.0419 0.3127 0.3945
11.000 1.3713 0.02791 0.02052 -0.0410 0.3092 0.3999
11.250 1.3882 0.02856 0.02124 -0.0403 0.3060 0.4064
11.500 1.4047 0.02927 0.02204 -0.0397 0.3025 0.4175
12.000 1.5800 0.03268 0.02653 -0.0713 0.2832 1.0000
12.250 1.5851 0.03407 0.02791 -0.0693 0.2763 1.0000
12.500 1.5938 0.03525 0.02912 -0.0678 0.2681 1.0000
12.750 1.5967 0.03689 0.03075 -0.0658 0.2589 1.0000
13.000 1.5985 0.03867 0.03252 -0.0638 0.2478 1.0000
13.250 1.5972 0.04078 0.03459 -0.0617 0.2337 1.0000
13.500 1.5950 0.04303 0.03682 -0.0598 0.2201 1.0000
13.750 1.5845 0.04613 0.03984 -0.0574 0.2018 1.0000
14.250 1.5706 0.05195 0.04561 -0.0538 0.1787 1.0000
14.500 1.5648 0.05487 0.04854 -0.0523 0.1703 1.0000
14.750 1.5603 0.05771 0.05138 -0.0510 0.1631 1.0000
15.000 1.5579 0.06036 0.05406 -0.0499 0.1585 1.0000
15.250 1.5581 0.06276 0.05652 -0.0489 0.1541 1.0000
15.500 1.5553 0.06551 0.05929 -0.0479 0.1489 1.0000
15.750 1.5502 0.06857 0.06239 -0.0470 0.1441 1.0000
16.000 1.5515 0.07095 0.06484 -0.0463 0.1398 1.0000
16.250 1.5485 0.07384 0.06777 -0.0456 0.1349 1.0000
16.500 1.5419 0.07718 0.07114 -0.0449 0.1294 1.0000
16.750 1.5409 0.07992 0.07392 -0.0444 0.1243 1.0000
17.000 1.5295 0.08395 0.07795 -0.0439 0.1154 1.0000
17.250 1.5241 0.08733 0.08138 -0.0435 0.1092 1.0000
17.500 1.5093 0.09191 0.08593 -0.0432 0.0989 1.0000
17.750 1.5000 0.09585 0.08990 -0.0431 0.0934 1.0000
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