USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 200,000 Max Cl/Cd: 50.48 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa32-il-200000-n5.txt Download as CSV file: xf-usa32-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.1668 0.10861 0.10442 -0.1362 0.9137 0.0334
-11.250 0.1684 0.10577 0.10158 -0.1382 0.9094 0.0344
-11.000 0.1719 0.10248 0.09828 -0.1418 0.9065 0.0346
-10.750 0.1864 0.09905 0.09486 -0.1442 0.9048 0.0348
-10.500 0.2092 0.09621 0.09200 -0.1455 0.9035 0.0355
-10.250 0.2292 0.09347 0.08924 -0.1484 0.9022 0.0369
-10.000 0.2395 0.09080 0.08657 -0.1507 0.8992 0.0388
-9.750 0.2225 0.08863 0.08443 -0.1515 0.8914 0.0400
-9.500 0.2388 0.08526 0.08105 -0.1540 0.8884 0.0404
-9.250 0.2660 0.08266 0.07843 -0.1558 0.8866 0.0414
-9.000 0.2905 0.07955 0.07528 -0.1604 0.8846 0.0430
-8.750 0.2838 0.07823 0.07400 -0.1575 0.8769 0.0434
-8.500 0.2889 0.07552 0.07129 -0.1595 0.8712 0.0450
-8.250 0.2872 0.07096 0.06670 -0.1668 0.8662 0.0461
-8.000 0.2599 0.07038 0.06619 -0.1601 0.8559 0.0462
-7.750 0.2862 0.06857 0.06438 -0.1599 0.8529 0.0473
-7.250 0.2475 0.06309 0.05890 -0.1538 0.8358 0.0397
-6.750 0.2510 0.06099 0.05683 -0.1486 0.8208 0.0425
-6.250 0.1980 0.05058 0.04626 -0.1428 0.7989 0.0350
-6.000 0.2091 0.05060 0.04629 -0.1402 0.7906 0.0358
-5.750 0.1265 0.03355 0.02827 -0.1352 0.7716 0.0348
-5.500 0.1361 0.03047 0.02475 -0.1335 0.7631 0.0348
-5.250 0.1378 0.02887 0.02291 -0.1292 0.7500 0.0350
-5.000 0.1512 0.02727 0.02108 -0.1270 0.7393 0.0353
-4.750 0.1738 0.02573 0.01927 -0.1263 0.7298 0.0356
-4.500 0.1933 0.02461 0.01794 -0.1249 0.7167 0.0362
-4.250 0.2182 0.02347 0.01651 -0.1244 0.7043 0.0371
-4.000 0.2453 0.02223 0.01488 -0.1242 0.6930 0.0377
-3.750 0.2725 0.02119 0.01349 -0.1239 0.6826 0.0380
-3.500 0.2982 0.02037 0.01236 -0.1233 0.6739 0.0384
-3.250 0.3256 0.01969 0.01138 -0.1230 0.6659 0.0388
-3.000 0.3515 0.01915 0.01061 -0.1225 0.6588 0.0391
-2.750 0.3775 0.01874 0.00999 -0.1220 0.6517 0.0396
-2.250 0.4302 0.01794 0.00897 -0.1212 0.6403 0.0412
-2.000 0.4553 0.01766 0.00863 -0.1206 0.6346 0.0417
-1.750 0.4840 0.01740 0.00826 -0.1207 0.6292 0.0423
-1.500 0.5080 0.01723 0.00805 -0.1199 0.6244 0.0428
-1.250 0.5295 0.01711 0.00791 -0.1185 0.6193 0.0434
-1.000 0.5542 0.01702 0.00776 -0.1178 0.6143 0.0440
-0.750 0.5834 0.01694 0.00758 -0.1180 0.6098 0.0449
-0.500 0.6036 0.01692 0.00753 -0.1165 0.6051 0.0458
-0.250 0.6233 0.01689 0.00749 -0.1148 0.6001 0.0470
0.000 0.6473 0.01686 0.00741 -0.1141 0.5954 0.0489
0.250 0.6760 0.01684 0.00729 -0.1142 0.5909 0.0511
0.500 0.6942 0.01687 0.00730 -0.1123 0.5858 0.0527
0.750 0.7127 0.01689 0.00732 -0.1104 0.5805 0.0549
1.000 0.7352 0.01688 0.00729 -0.1093 0.5755 0.0599
1.250 0.7627 0.01659 0.00735 -0.1095 0.5710 0.1676
1.500 0.7765 0.01674 0.00759 -0.1068 0.5657 0.2011
1.750 0.7931 0.01691 0.00779 -0.1046 0.5600 0.2213
2.000 0.8133 0.01706 0.00790 -0.1032 0.5548 0.2325
2.250 0.8298 0.01723 0.00808 -0.1010 0.5490 0.2414
2.500 0.8441 0.01743 0.00829 -0.0985 0.5424 0.2491
2.750 0.8621 0.01760 0.00841 -0.0967 0.5364 0.2581
3.000 0.8766 0.01782 0.00868 -0.0942 0.5298 0.2664
3.250 0.8914 0.01805 0.00890 -0.0919 0.5229 0.2762
3.500 0.9080 0.01826 0.00911 -0.0899 0.5168 0.2834
3.750 0.9223 0.01850 0.00937 -0.0876 0.5092 0.2896
4.000 0.9381 0.01872 0.00953 -0.0855 0.5021 0.2943
4.250 0.9531 0.01896 0.00980 -0.0834 0.4943 0.2980
4.500 0.9681 0.01922 0.01004 -0.0812 0.4864 0.3025
4.750 0.9836 0.01951 0.01031 -0.0793 0.4789 0.3073
5.000 0.9990 0.01982 0.01057 -0.0773 0.4713 0.3132
5.250 1.0156 0.02012 0.01087 -0.0756 0.4644 0.3181
5.500 1.0319 0.02047 0.01122 -0.0739 0.4573 0.3247
5.750 1.0487 0.02083 0.01150 -0.0724 0.4510 0.3319
6.000 1.0665 0.02119 0.01189 -0.0710 0.4447 0.3373
6.250 1.0844 0.02156 0.01225 -0.0698 0.4387 0.3441
6.500 1.1033 0.02194 0.01256 -0.0687 0.4336 0.3504
6.750 1.1209 0.02235 0.01301 -0.0675 0.4277 0.3572
7.000 1.1375 0.02281 0.01344 -0.0661 0.4215 0.3643
7.250 1.1567 0.02320 0.01380 -0.0652 0.4167 0.3708
7.500 1.1729 0.02369 0.01431 -0.0638 0.4109 0.3787
7.750 1.1898 0.02417 0.01480 -0.0626 0.4054 0.3854
8.000 1.2082 0.02462 0.01524 -0.0617 0.4012 0.3942
8.250 1.2268 0.02508 0.01570 -0.0609 0.3968 0.4020
8.500 1.2429 0.02563 0.01631 -0.0597 0.3918 0.4104
8.750 1.2596 0.02618 0.01690 -0.0587 0.3870 0.4196
9.000 1.2772 0.02672 0.01743 -0.0578 0.3824 0.4325
9.250 1.2989 0.02717 0.01809 -0.0580 0.3785 0.5219
9.750 1.4473 0.02932 0.02116 -0.0815 0.3670 1.0000
10.000 1.4616 0.02994 0.02175 -0.0800 0.3634 1.0000
10.250 1.4733 0.03069 0.02258 -0.0782 0.3596 1.0000
10.500 1.4839 0.03151 0.02347 -0.0764 0.3556 1.0000
10.750 1.4942 0.03235 0.02434 -0.0746 0.3511 1.0000
11.000 1.5051 0.03316 0.02515 -0.0729 0.3470 1.0000
11.250 1.5155 0.03405 0.02607 -0.0712 0.3430 1.0000
11.500 1.5243 0.03506 0.02719 -0.0694 0.3388 1.0000
11.750 1.5326 0.03610 0.02829 -0.0676 0.3345 1.0000
12.000 1.5425 0.03707 0.02929 -0.0660 0.3307 1.0000
12.250 1.5515 0.03811 0.03034 -0.0643 0.3265 1.0000
12.500 1.5578 0.03940 0.03177 -0.0626 0.3222 1.0000
12.750 1.5630 0.04077 0.03322 -0.0608 0.3171 1.0000
13.000 1.5685 0.04213 0.03458 -0.0591 0.3119 1.0000
13.250 1.5731 0.04365 0.03620 -0.0575 0.3070 1.0000
13.500 1.5759 0.04536 0.03801 -0.0558 0.3013 1.0000
13.750 1.5779 0.04714 0.03981 -0.0541 0.2952 1.0000
14.000 1.5807 0.04897 0.04174 -0.0527 0.2901 1.0000
14.250 1.5813 0.05107 0.04393 -0.0513 0.2837 1.0000
14.500 1.5799 0.05335 0.04624 -0.0498 0.2764 1.0000
14.750 1.5795 0.05570 0.04872 -0.0486 0.2695 1.0000
15.000 1.5750 0.05843 0.05146 -0.0473 0.2611 1.0000
15.250 1.5697 0.06140 0.05452 -0.0462 0.2512 1.0000
15.500 1.5628 0.06456 0.05771 -0.0451 0.2406 1.0000
15.750 1.5544 0.06794 0.06111 -0.0441 0.2299 1.0000
16.000 1.5428 0.07172 0.06490 -0.0432 0.2178 1.0000
16.250 1.5325 0.07544 0.06864 -0.0424 0.2068 1.0000
16.500 1.5222 0.07922 0.07243 -0.0417 0.1978 1.0000
16.750 1.5075 0.08360 0.07680 -0.0411 0.1887 1.0000
17.000 1.4985 0.08736 0.08060 -0.0407 0.1814 1.0000
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