USA 32 AIRFOIL (usa32-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 32 AIRFOIL (usa32-il) Reynolds number: 500,000 Max Cl/Cd: 68.86 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa32-il-500000.txt Download as CSV file: xf-usa32-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 0.1811 0.10783 0.10510 -0.1466 0.9419 0.0256
-12.000 0.1818 0.10396 0.10122 -0.1509 0.9384 0.0263
-11.750 0.1917 0.09992 0.09717 -0.1540 0.9363 0.0266
-11.500 0.2131 0.09726 0.09450 -0.1556 0.9347 0.0268
-11.250 0.2334 0.09447 0.09169 -0.1586 0.9332 0.0271
-11.000 0.2545 0.09159 0.08879 -0.1623 0.9318 0.0277
-10.750 0.2687 0.08893 0.08612 -0.1647 0.9284 0.0283
-10.500 0.2782 0.08627 0.08345 -0.1664 0.9238 0.0295
-10.250 0.2794 0.08034 0.07749 -0.1755 0.9196 0.0308
-10.000 0.3045 0.07756 0.07469 -0.1782 0.9179 0.0311
-9.750 0.3337 0.07524 0.07235 -0.1816 0.9163 0.0316
-9.500 0.3496 0.07338 0.07047 -0.1832 0.9124 0.0322
-9.250 0.3593 0.07129 0.06838 -0.1842 0.9074 0.0334
-9.000 0.3586 0.06469 0.06174 -0.1944 0.9013 0.0358
-8.750 0.3763 0.06283 0.05985 -0.1951 0.8970 0.0361
-8.500 0.3848 0.06197 0.05900 -0.1931 0.8910 0.0365
-8.250 0.3991 0.06003 0.05704 -0.1946 0.8861 0.0370
-8.000 0.4144 0.05784 0.05481 -0.1972 0.8815 0.0380
-7.750 0.4039 0.05638 0.05338 -0.1943 0.8732 0.0386
-7.500 0.3566 0.04983 0.04677 -0.1954 0.8628 0.0413
-7.250 0.3621 0.04934 0.04630 -0.1919 0.8568 0.0417
-7.000 0.3786 0.04861 0.04554 -0.1911 0.8515 0.0422
-6.750 0.3835 0.04738 0.04429 -0.1891 0.8442 0.0428
-6.500 0.3393 0.03665 0.03330 -0.1902 0.8339 0.0479
-6.250 0.3499 0.03704 0.03374 -0.1863 0.8255 0.0481
-6.000 0.3660 0.03694 0.03360 -0.1842 0.8165 0.0485
-5.750 0.3694 0.03666 0.03330 -0.1798 0.8049 0.0489
-5.500 0.3771 0.03566 0.03225 -0.1770 0.7933 0.0497
-5.250 0.3346 0.02589 0.02176 -0.1711 0.7799 0.0559
-5.000 0.3358 0.02543 0.02132 -0.1656 0.7636 0.0566
-4.750 0.3337 0.02472 0.02053 -0.1596 0.7426 0.0574
-4.500 0.3345 0.02395 0.01958 -0.1544 0.7182 0.0589
-4.250 0.3237 0.02218 0.01724 -0.1473 0.6962 0.0643
-4.000 0.3340 0.02169 0.01672 -0.1439 0.6808 0.0656
-3.750 0.3458 0.02123 0.01613 -0.1408 0.6696 0.0683
-3.500 0.3545 0.02024 0.01485 -0.1373 0.6615 0.0748
-3.250 0.3716 0.01974 0.01432 -0.1353 0.6544 0.0771
-2.750 0.4005 0.01476 0.00767 -0.1267 0.6441 0.0417
-2.500 0.4225 0.01429 0.00713 -0.1254 0.6392 0.0420
-2.250 0.4465 0.01396 0.00670 -0.1245 0.6343 0.0422
-2.000 0.4730 0.01366 0.00632 -0.1241 0.6294 0.0425
-1.750 0.4941 0.01343 0.00607 -0.1226 0.6256 0.0425
-1.500 0.5162 0.01322 0.00585 -0.1213 0.6214 0.0429
-1.250 0.5407 0.01306 0.00564 -0.1205 0.6172 0.0434
-1.000 0.5700 0.01294 0.00545 -0.1207 0.6128 0.0439
-0.750 0.5904 0.01283 0.00535 -0.1191 0.6088 0.0444
-0.500 0.6101 0.01275 0.00527 -0.1173 0.6046 0.0454
-0.250 0.6319 0.01270 0.00520 -0.1159 0.6004 0.0464
0.000 0.6576 0.01267 0.00511 -0.1154 0.5962 0.0470
0.250 0.6849 0.01261 0.00500 -0.1153 0.5921 0.0481
0.500 0.7016 0.01254 0.00497 -0.1129 0.5882 0.0493
0.750 0.7210 0.01250 0.00493 -0.1111 0.5838 0.0519
1.000 0.7418 0.01253 0.00490 -0.1096 0.5791 0.0538
1.250 0.7689 0.01255 0.00488 -0.1095 0.5743 0.0590
1.500 0.7810 0.01225 0.00500 -0.1064 0.5699 0.1789
1.750 0.7967 0.01233 0.00516 -0.1039 0.5648 0.2122
2.000 0.8153 0.01245 0.00528 -0.1020 0.5597 0.2280
2.250 0.8353 0.01260 0.00539 -0.1005 0.5547 0.2390
2.500 0.8495 0.01270 0.00555 -0.0978 0.5490 0.2473
2.750 0.8656 0.01284 0.00567 -0.0955 0.5431 0.2535
3.000 0.8828 0.01298 0.00579 -0.0934 0.5373 0.2612
3.250 0.8975 0.01313 0.00598 -0.0910 0.5302 0.2679
3.500 0.9121 0.01331 0.00612 -0.0885 0.5231 0.2726
3.750 0.9276 0.01347 0.00629 -0.0862 0.5153 0.2779
4.000 0.9411 0.01371 0.00653 -0.0836 0.5066 0.2856
4.250 0.9564 0.01394 0.00675 -0.0813 0.4979 0.2914
4.500 0.9699 0.01421 0.00699 -0.0788 0.4886 0.2977
4.750 0.9851 0.01448 0.00726 -0.0767 0.4794 0.3031
5.000 0.9982 0.01484 0.00753 -0.0742 0.4701 0.3091
5.250 1.0149 0.01510 0.00780 -0.0724 0.4613 0.3146
5.500 1.0285 0.01549 0.00814 -0.0701 0.4526 0.3204
5.750 1.0453 0.01581 0.00845 -0.0684 0.4445 0.3273
6.000 1.0611 0.01617 0.00877 -0.0665 0.4377 0.3332
6.250 1.0785 0.01649 0.00910 -0.0650 0.4307 0.3402
6.500 1.0943 0.01688 0.00945 -0.0633 0.4238 0.3473
6.750 1.1106 0.01726 0.00983 -0.0617 0.4176 0.3539
7.000 1.1287 0.01760 0.01018 -0.0603 0.4119 0.3613
7.250 1.1455 0.01797 0.01055 -0.0589 0.4064 0.3681
7.500 1.1625 0.01838 0.01092 -0.0575 0.4015 0.3753
7.750 1.1811 0.01869 0.01131 -0.0564 0.3971 0.3819
8.000 1.1991 0.01906 0.01169 -0.0552 0.3926 0.3887
8.250 1.2163 0.01948 0.01209 -0.0540 0.3881 0.3953
8.500 1.2352 0.01986 0.01249 -0.0530 0.3841 0.4027
8.750 1.2532 0.02024 0.01294 -0.0520 0.3802 0.4096
9.000 1.2718 0.02062 0.01338 -0.0511 0.3765 0.4180
9.250 1.2896 0.02107 0.01385 -0.0502 0.3724 0.4282
9.500 1.3094 0.02149 0.01429 -0.0496 0.3682 0.4464
9.750 1.5016 0.02288 0.01682 -0.0878 0.3578 1.0000
10.000 1.5141 0.02352 0.01743 -0.0859 0.3535 1.0000
10.250 1.5281 0.02410 0.01803 -0.0843 0.3496 1.0000
10.500 1.5421 0.02467 0.01866 -0.0827 0.3458 1.0000
10.750 1.5550 0.02532 0.01934 -0.0811 0.3418 1.0000
11.000 1.5660 0.02608 0.02008 -0.0792 0.3373 1.0000
11.250 1.5789 0.02678 0.02078 -0.0776 0.3336 1.0000
11.500 1.5918 0.02747 0.02157 -0.0761 0.3300 1.0000
11.750 1.6030 0.02828 0.02241 -0.0744 0.3250 1.0000
12.000 1.6114 0.02926 0.02338 -0.0725 0.3201 1.0000
12.250 1.6207 0.03024 0.02441 -0.0707 0.3140 1.0000
12.500 1.6306 0.03121 0.02543 -0.0691 0.3084 1.0000
12.750 1.6368 0.03243 0.02663 -0.0671 0.3032 1.0000
13.000 1.6474 0.03341 0.02768 -0.0657 0.2983 1.0000
13.250 1.6557 0.03457 0.02890 -0.0641 0.2925 1.0000
13.500 1.6589 0.03612 0.03043 -0.0621 0.2861 1.0000
13.750 1.6685 0.03728 0.03167 -0.0608 0.2801 1.0000
14.000 1.6703 0.03904 0.03344 -0.0589 0.2719 1.0000
14.250 1.6751 0.04063 0.03508 -0.0574 0.2633 1.0000
14.500 1.6743 0.04274 0.03719 -0.0556 0.2549 1.0000
14.750 1.6737 0.04493 0.03939 -0.0540 0.2427 1.0000
15.000 1.6707 0.04739 0.04185 -0.0523 0.2309 1.0000
15.250 1.6625 0.05040 0.04483 -0.0505 0.2168 1.0000
15.500 1.6519 0.05373 0.04813 -0.0488 0.2036 1.0000
15.750 1.6408 0.05718 0.05157 -0.0473 0.1926 1.0000
16.000 1.6285 0.06080 0.05516 -0.0458 0.1826 1.0000
16.250 1.6224 0.06383 0.05822 -0.0446 0.1756 1.0000
16.500 1.6121 0.06736 0.06176 -0.0435 0.1692 1.0000
16.750 1.6067 0.07043 0.06487 -0.0426 0.1633 1.0000
17.000 1.6004 0.07363 0.06810 -0.0418 0.1578 1.0000
17.250 1.5902 0.07732 0.07182 -0.0411 0.1528 1.0000
17.500 1.5897 0.07998 0.07455 -0.0406 0.1479 1.0000
17.750 1.5806 0.08368 0.07828 -0.0402 0.1423 1.0000
18.000 1.5744 0.08711 0.08175 -0.0398 0.1382 1.0000
18.250 1.5710 0.09022 0.08492 -0.0397 0.1320 1.0000
18.500 1.5591 0.09443 0.08915 -0.0395 0.1263 1.0000
18.750 1.5554 0.09767 0.09245 -0.0395 0.1203 1.0000
19.000 1.5429 0.10209 0.09688 -0.0397 0.1138 1.0000
19.250 1.5370 0.10565 0.10049 -0.0399 0.1076 1.0000
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