USA 33 AIRFOIL (usa33-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: USA 33 AIRFOIL (usa33-il) Reynolds number: 500,000 Max Cl/Cd: 85.32 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa33-il-500000.txt Download as CSV file: xf-usa33-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1734 0.11990 0.11759 -0.0358 1.0000 0.0427
-11.500 -0.1718 0.11723 0.11495 -0.0360 1.0000 0.0436
-11.250 -0.2007 0.10934 0.10704 -0.0426 0.9991 0.0452
-11.000 -0.1789 0.10585 0.10355 -0.0443 0.9902 0.0454
-10.750 -0.1578 0.10264 0.10034 -0.0463 0.9777 0.0456
-10.500 -0.1356 0.09915 0.09685 -0.0494 0.9595 0.0460
-10.250 -0.1088 0.09463 0.09229 -0.0552 0.9424 0.0466
-10.000 -0.0783 0.08917 0.08678 -0.0631 0.9270 0.0476
-9.750 -0.0876 0.07873 0.07625 -0.0749 0.9123 0.0503
-9.500 -0.0433 0.07432 0.07169 -0.0825 0.8804 0.0506
-9.250 -0.0202 0.07161 0.06877 -0.0851 0.8454 0.0511
-9.000 -0.0125 0.06927 0.06630 -0.0855 0.8222 0.0516
-8.750 -0.0090 0.06672 0.06368 -0.0857 0.8049 0.0523
-8.500 -0.0097 0.06379 0.06068 -0.0861 0.7903 0.0532
-8.250 -0.0868 0.06321 0.06006 -0.1006 0.8161 0.0549
-8.000 -0.2942 0.03532 0.03113 -0.0906 0.7975 0.0504
-7.750 -0.2799 0.03411 0.02986 -0.0887 0.7852 0.0497
-7.500 -0.2901 0.02986 0.02521 -0.0843 0.7732 0.0491
-7.250 -0.2965 0.02600 0.02083 -0.0797 0.7615 0.0489
-7.000 -0.2893 0.02387 0.01825 -0.0764 0.7499 0.0492
-6.750 -0.2761 0.02244 0.01650 -0.0738 0.7372 0.0495
-6.500 -0.2599 0.02174 0.01545 -0.0714 0.7246 0.0500
-6.250 -0.2429 0.02016 0.01364 -0.0695 0.7110 0.0505
-6.000 -0.2213 0.01927 0.01268 -0.0683 0.6969 0.0511
-5.750 -0.1987 0.01867 0.01199 -0.0672 0.6832 0.0516
-5.500 -0.1761 0.01809 0.01129 -0.0660 0.6695 0.0521
-5.250 -0.1531 0.01749 0.01055 -0.0648 0.6569 0.0526
-4.750 -0.1054 0.01645 0.00922 -0.0627 0.6358 0.0537
-4.500 -0.0811 0.01603 0.00863 -0.0617 0.6264 0.0543
-4.250 -0.0562 0.01572 0.00820 -0.0608 0.6179 0.0550
-4.000 -0.0308 0.01516 0.00752 -0.0601 0.6095 0.0558
-3.750 -0.0047 0.01461 0.00694 -0.0596 0.6021 0.0565
-3.500 0.0217 0.01422 0.00655 -0.0591 0.5956 0.0573
-3.250 0.0479 0.01390 0.00619 -0.0585 0.5896 0.0580
-3.000 0.0738 0.01365 0.00587 -0.0578 0.5837 0.0589
-2.750 0.1003 0.01338 0.00558 -0.0573 0.5786 0.0597
-2.500 0.1265 0.01314 0.00532 -0.0566 0.5733 0.0605
-2.250 0.1524 0.01290 0.00503 -0.0560 0.5681 0.0613
-2.000 0.1775 0.01257 0.00470 -0.0552 0.5633 0.0626
-1.750 0.2029 0.01236 0.00452 -0.0545 0.5591 0.0639
-1.500 0.2283 0.01216 0.00435 -0.0537 0.5548 0.0651
-1.250 0.2535 0.01201 0.00419 -0.0529 0.5502 0.0663
-1.000 0.2782 0.01187 0.00402 -0.0519 0.5455 0.0675
-0.750 0.3023 0.01173 0.00389 -0.0510 0.5404 0.0694
-0.500 0.3269 0.01157 0.00378 -0.0500 0.5362 0.0717
-0.250 0.3516 0.01147 0.00369 -0.0491 0.5314 0.0739
0.000 0.3755 0.01135 0.00360 -0.0480 0.5265 0.0778
0.250 0.3997 0.01133 0.00356 -0.0470 0.5208 0.0832
0.500 0.4232 0.01117 0.00355 -0.0459 0.5161 0.1006
0.750 0.4478 0.01112 0.00362 -0.0450 0.5102 0.1303
1.000 0.4733 0.01121 0.00370 -0.0443 0.5038 0.1451
1.250 0.4990 0.01130 0.00377 -0.0436 0.4971 0.1542
1.500 0.5244 0.01132 0.00384 -0.0428 0.4896 0.1615
1.750 0.5488 0.01142 0.00386 -0.0419 0.4813 0.1663
2.000 0.5730 0.01138 0.00388 -0.0409 0.4734 0.1719
2.250 0.5970 0.01143 0.00391 -0.0399 0.4640 0.1772
2.500 0.6213 0.01148 0.00394 -0.0390 0.4550 0.1814
2.750 0.6432 0.01145 0.00390 -0.0376 0.4440 0.1858
3.000 0.6660 0.01147 0.00392 -0.0364 0.4315 0.1903
3.250 0.6879 0.01155 0.00395 -0.0351 0.4173 0.1950
3.500 0.7088 0.01165 0.00398 -0.0335 0.4025 0.1989
3.750 0.7285 0.01171 0.00402 -0.0318 0.3877 0.2045
4.000 0.7491 0.01184 0.00411 -0.0303 0.3743 0.2106
4.250 0.7688 0.01198 0.00420 -0.0286 0.3630 0.2163
4.500 0.7878 0.01210 0.00431 -0.0268 0.3528 0.2234
4.750 0.8080 0.01225 0.00442 -0.0252 0.3446 0.2303
5.000 0.8269 0.01236 0.00454 -0.0234 0.3365 0.2386
5.250 0.8454 0.01251 0.00468 -0.0215 0.3293 0.2494
5.500 0.8630 0.01251 0.00482 -0.0195 0.3221 0.2937
5.750 0.9504 0.01178 0.00569 -0.0323 0.3095 0.9620
6.000 0.9959 0.01228 0.00614 -0.0360 0.2998 0.9757
6.250 1.0415 0.01271 0.00650 -0.0398 0.2902 0.9826
6.500 1.0853 0.01312 0.00685 -0.0434 0.2795 0.9881
6.750 1.1261 0.01345 0.00714 -0.0462 0.2695 0.9927
7.000 1.1689 0.01378 0.00740 -0.0497 0.2581 0.9962
7.250 1.2064 0.01414 0.00767 -0.0522 0.2438 0.9992
7.500 1.2258 0.01442 0.00790 -0.0508 0.2313 1.0000
7.750 1.2321 0.01471 0.00815 -0.0469 0.2209 1.0000
8.000 1.2327 0.01503 0.00841 -0.0418 0.2102 1.0000
8.250 1.2289 0.01535 0.00867 -0.0359 0.1999 1.0000
8.500 1.2289 0.01570 0.00899 -0.0309 0.1916 1.0000
8.750 1.2290 0.01617 0.00940 -0.0261 0.1826 1.0000
9.000 1.2323 0.01666 0.00986 -0.0220 0.1745 1.0000
9.250 1.2362 0.01723 0.01039 -0.0182 0.1671 1.0000
9.500 1.2407 0.01787 0.01100 -0.0147 0.1596 1.0000
9.750 1.2473 0.01852 0.01163 -0.0117 0.1530 1.0000
10.000 1.2526 0.01931 0.01239 -0.0087 0.1457 1.0000
10.250 1.2599 0.02010 0.01317 -0.0062 0.1374 1.0000
10.500 1.2658 0.02105 0.01410 -0.0038 0.1289 1.0000
10.750 1.2658 0.02245 0.01540 -0.0011 0.1102 1.0000
11.000 1.2509 0.02498 0.01771 0.0023 0.0792 1.0000
11.250 1.2502 0.02677 0.01948 0.0044 0.0733 1.0000
11.500 1.2541 0.02832 0.02105 0.0059 0.0708 1.0000
11.750 1.2593 0.02986 0.02262 0.0072 0.0693 1.0000
12.000 1.2643 0.03148 0.02428 0.0083 0.0681 1.0000
12.250 1.2690 0.03318 0.02603 0.0093 0.0673 1.0000
12.500 1.2721 0.03509 0.02799 0.0102 0.0665 1.0000
12.750 1.2747 0.03711 0.03007 0.0110 0.0659 1.0000
13.000 1.2762 0.03929 0.03230 0.0117 0.0653 1.0000
13.250 1.2773 0.04158 0.03465 0.0123 0.0648 1.0000
13.500 1.2765 0.04413 0.03726 0.0127 0.0642 1.0000
13.750 1.2754 0.04679 0.03997 0.0130 0.0638 1.0000
14.000 1.2724 0.04972 0.04297 0.0132 0.0634 1.0000
14.250 1.2735 0.05227 0.04559 0.0134 0.0632 1.0000
14.500 1.2740 0.05491 0.04831 0.0134 0.0630 1.0000
14.750 1.2741 0.05763 0.05109 0.0134 0.0627 1.0000
15.000 1.2727 0.06060 0.05413 0.0133 0.0625 1.0000
15.250 1.2725 0.06345 0.05705 0.0131 0.0623 1.0000
15.500 1.2710 0.06648 0.06015 0.0129 0.0621 1.0000
15.750 1.2700 0.06950 0.06324 0.0126 0.0620 1.0000
16.000 1.2685 0.07262 0.06642 0.0122 0.0616 1.0000
16.250 1.2675 0.07572 0.06958 0.0118 0.0616 1.0000
16.500 1.2671 0.07873 0.07266 0.0113 0.0613 1.0000
16.750 1.2667 0.08181 0.07579 0.0108 0.0611 1.0000
17.000 1.2668 0.08480 0.07884 0.0103 0.0609 1.0000
17.250 1.2677 0.08773 0.08182 0.0098 0.0608 1.0000
17.500 1.2688 0.09062 0.08476 0.0092 0.0606 1.0000
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Polar data table (+)
Polar graphs
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