USA 33 AIRFOIL (usa33-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: USA 33 AIRFOIL (usa33-il) Reynolds number: 200,000 Max Cl/Cd: 60.48 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa33-il-200000-n5.txt Download as CSV file: xf-usa33-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.2463 0.11594 0.11199 -0.0375 1.0000 0.0536
-10.750 -0.2498 0.11254 0.10863 -0.0388 1.0000 0.0538
-10.500 -0.2583 0.10715 0.10325 -0.0404 1.0000 0.0488
-10.250 -0.2371 0.10476 0.10090 -0.0407 0.9900 0.0484
-10.000 -0.2179 0.10156 0.09770 -0.0430 0.9743 0.0473
-9.750 -0.2047 0.09685 0.09297 -0.0477 0.9489 0.0461
-9.500 -0.1843 0.09140 0.08747 -0.0551 0.9238 0.0460
-9.250 -0.1558 0.08582 0.08180 -0.0644 0.9005 0.0464
-9.000 -0.1291 0.07950 0.07534 -0.0749 0.8766 0.0464
-8.750 -0.1108 0.07341 0.06910 -0.0840 0.8515 0.0461
-8.500 -0.1088 0.06787 0.06342 -0.0905 0.8284 0.0460
-8.250 -0.1231 0.06314 0.05856 -0.0935 0.8085 0.0459
-8.000 -0.1444 0.05931 0.05460 -0.0923 0.7917 0.0458
-7.750 -0.1593 0.05600 0.05115 -0.0906 0.7769 0.0461
-7.500 -0.1720 0.05222 0.04722 -0.0888 0.7639 0.0466
-7.250 -0.2899 0.03025 0.02351 -0.0793 0.7565 0.0482
-7.000 -0.2870 0.02739 0.01996 -0.0758 0.7453 0.0488
-6.750 -0.2678 0.02651 0.01901 -0.0744 0.7336 0.0493
-6.500 -0.2482 0.02573 0.01814 -0.0729 0.7221 0.0498
-6.250 -0.2280 0.02496 0.01723 -0.0715 0.7114 0.0504
-6.000 -0.2081 0.02411 0.01622 -0.0701 0.7004 0.0511
-5.750 -0.1878 0.02319 0.01504 -0.0686 0.6904 0.0518
-5.500 -0.1666 0.02228 0.01390 -0.0673 0.6802 0.0524
-5.250 -0.1444 0.02149 0.01284 -0.0660 0.6708 0.0530
-5.000 -0.1214 0.02080 0.01190 -0.0649 0.6615 0.0537
-4.750 -0.0974 0.02016 0.01114 -0.0640 0.6521 0.0542
-4.500 -0.0729 0.01964 0.01059 -0.0632 0.6433 0.0550
-4.250 -0.0484 0.01920 0.01009 -0.0624 0.6340 0.0559
-4.000 -0.0236 0.01879 0.00956 -0.0615 0.6257 0.0568
-3.750 0.0016 0.01835 0.00903 -0.0608 0.6168 0.0578
-3.500 0.0268 0.01797 0.00852 -0.0600 0.6084 0.0585
-3.250 0.0524 0.01762 0.00806 -0.0592 0.6004 0.0592
-3.000 0.0774 0.01722 0.00767 -0.0585 0.5924 0.0600
-2.750 0.1024 0.01692 0.00735 -0.0577 0.5858 0.0610
-2.500 0.1277 0.01665 0.00708 -0.0570 0.5800 0.0623
-2.250 0.1531 0.01640 0.00681 -0.0563 0.5740 0.0637
-2.000 0.1783 0.01620 0.00655 -0.0555 0.5681 0.0649
-1.750 0.2030 0.01599 0.00631 -0.0546 0.5631 0.0662
-1.500 0.2279 0.01578 0.00615 -0.0538 0.5579 0.0675
-1.250 0.2528 0.01562 0.00600 -0.0530 0.5526 0.0691
-1.000 0.2777 0.01549 0.00583 -0.0521 0.5476 0.0710
-0.750 0.3022 0.01536 0.00571 -0.0512 0.5427 0.0737
-0.500 0.3267 0.01523 0.00561 -0.0503 0.5375 0.0772
-0.250 0.3508 0.01510 0.00556 -0.0494 0.5316 0.0816
0.000 0.3746 0.01500 0.00551 -0.0483 0.5259 0.0892
0.250 0.3987 0.01496 0.00551 -0.0474 0.5210 0.1041
0.500 0.4233 0.01496 0.00560 -0.0465 0.5157 0.1230
0.750 0.4480 0.01501 0.00570 -0.0456 0.5098 0.1369
1.000 0.4726 0.01509 0.00575 -0.0447 0.5041 0.1474
1.250 0.4974 0.01520 0.00580 -0.0439 0.4987 0.1564
1.500 0.5212 0.01523 0.00589 -0.0429 0.4915 0.1633
1.750 0.5447 0.01528 0.00593 -0.0418 0.4836 0.1700
2.000 0.5677 0.01533 0.00594 -0.0406 0.4760 0.1760
2.250 0.5905 0.01534 0.00600 -0.0395 0.4671 0.1818
2.500 0.6128 0.01539 0.00599 -0.0382 0.4587 0.1869
2.750 0.6345 0.01537 0.00603 -0.0368 0.4487 0.1922
3.000 0.6550 0.01540 0.00603 -0.0352 0.4380 0.1979
3.500 0.6946 0.01544 0.00607 -0.0318 0.4115 0.2102
3.750 0.7129 0.01552 0.00609 -0.0298 0.3971 0.2165
4.000 0.7301 0.01564 0.00613 -0.0277 0.3828 0.2214
4.250 0.7473 0.01576 0.00621 -0.0255 0.3696 0.2266
4.500 0.7653 0.01591 0.00631 -0.0236 0.3600 0.2332
4.750 0.7819 0.01608 0.00645 -0.0214 0.3500 0.2412
5.000 0.7993 0.01624 0.00661 -0.0194 0.3417 0.2533
5.250 0.8151 0.01637 0.00679 -0.0171 0.3336 0.2804
6.750 1.1014 0.01821 0.00992 -0.0435 0.2698 1.0000
7.000 1.1108 0.01849 0.01019 -0.0402 0.2627 1.0000
7.250 1.1145 0.01882 0.01048 -0.0359 0.2556 1.0000
7.500 1.1197 0.01909 0.01075 -0.0318 0.2487 1.0000
7.750 1.1229 0.01943 0.01106 -0.0274 0.2414 1.0000
8.000 1.1281 0.01981 0.01142 -0.0236 0.2345 1.0000
8.250 1.1341 0.02024 0.01183 -0.0200 0.2267 1.0000
8.500 1.1400 0.02075 0.01232 -0.0166 0.2195 1.0000
8.750 1.1461 0.02132 0.01287 -0.0134 0.2110 1.0000
9.000 1.1521 0.02198 0.01351 -0.0104 0.2032 1.0000
9.250 1.1572 0.02276 0.01425 -0.0075 0.1951 1.0000
9.500 1.1635 0.02358 0.01505 -0.0049 0.1885 1.0000
9.750 1.1688 0.02453 0.01598 -0.0025 0.1816 1.0000
10.000 1.1737 0.02560 0.01703 -0.0002 0.1745 1.0000
10.250 1.1793 0.02672 0.01815 0.0018 0.1686 1.0000
10.500 1.1846 0.02794 0.01936 0.0036 0.1634 1.0000
10.750 1.1922 0.02909 0.02053 0.0052 0.1584 1.0000
11.000 1.1965 0.03051 0.02196 0.0068 0.1532 1.0000
11.250 1.2035 0.03181 0.02329 0.0081 0.1485 1.0000
11.500 1.2092 0.03327 0.02478 0.0093 0.1425 1.0000
11.750 1.2131 0.03493 0.02645 0.0105 0.1349 1.0000
12.000 1.2164 0.03671 0.02824 0.0115 0.1275 1.0000
12.250 1.2190 0.03861 0.03016 0.0124 0.1168 1.0000
12.750 1.1975 0.04514 0.03645 0.0141 0.0796 1.0000
13.000 1.1923 0.04808 0.03938 0.0146 0.0748 1.0000
13.250 1.1910 0.05072 0.04205 0.0150 0.0729 1.0000
13.500 1.1898 0.05344 0.04482 0.0152 0.0713 1.0000
13.750 1.1878 0.05631 0.04775 0.0153 0.0701 1.0000
14.000 1.1857 0.05927 0.05077 0.0152 0.0691 1.0000
14.250 1.1832 0.06235 0.05393 0.0151 0.0683 1.0000
14.500 1.1818 0.06537 0.05702 0.0149 0.0678 1.0000
14.750 1.1798 0.06852 0.06025 0.0146 0.0672 1.0000
15.000 1.1766 0.07187 0.06369 0.0141 0.0666 1.0000
15.250 1.1735 0.07529 0.06720 0.0136 0.0663 1.0000
15.500 1.1695 0.07888 0.07088 0.0129 0.0659 1.0000
15.750 1.1655 0.08253 0.07462 0.0122 0.0655 1.0000
16.000 1.1609 0.08634 0.07852 0.0114 0.0652 1.0000
16.250 1.1557 0.09028 0.08254 0.0104 0.0647 1.0000
16.500 1.1519 0.09404 0.08638 0.0095 0.0645 1.0000
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