WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il) Reynolds number: 200,000 Max Cl/Cd: 56.07 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx72150b-il-200000.txt Download as CSV file: xf-fx72150b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 72-MS-150B 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.2932 0.10010 0.09529 -0.1570 0.7744 0.0309
-10.000 0.2985 0.09840 0.09354 -0.1586 0.7705 0.0315
-9.750 0.2965 0.09761 0.09281 -0.1601 0.7648 0.0317
-9.500 0.3087 0.09440 0.08958 -0.1604 0.7601 0.0320
-9.250 0.3246 0.09125 0.08636 -0.1604 0.7565 0.0327
-9.000 0.3337 0.08919 0.08430 -0.1609 0.7519 0.0333
-8.750 0.3422 0.08719 0.08231 -0.1614 0.7471 0.0342
-8.500 0.3507 0.08509 0.08017 -0.1623 0.7432 0.0352
-8.250 0.3569 0.08324 0.07828 -0.1636 0.7395 0.0365
-8.000 0.3566 0.08210 0.07720 -0.1649 0.7340 0.0369
-7.750 0.3570 0.08026 0.07537 -0.1666 0.7296 0.0373
-7.500 0.3787 0.07694 0.07195 -0.1656 0.7265 0.0382
-7.250 0.3889 0.07509 0.07010 -0.1657 0.7224 0.0393
-7.000 0.3953 0.07342 0.06846 -0.1659 0.7176 0.0411
-6.750 0.3935 0.07217 0.06723 -0.1676 0.7134 0.0429
-6.500 0.3875 0.07126 0.06632 -0.1703 0.7099 0.0433
-6.250 0.4029 0.06820 0.06325 -0.1680 0.7066 0.0440
-6.000 0.4128 0.06646 0.06155 -0.1669 0.7024 0.0450
-5.750 0.4213 0.06481 0.05990 -0.1671 0.6987 0.0462
-5.500 0.4316 0.06295 0.05801 -0.1686 0.6957 0.0478
-5.250 0.4495 0.06009 0.05509 -0.1818 0.6926 0.0505
-5.000 0.4571 0.05759 0.05268 -0.1821 0.6887 0.0510
-4.750 0.4649 0.05621 0.05133 -0.1782 0.6853 0.0519
-4.500 0.4797 0.05451 0.04961 -0.1784 0.6823 0.0535
-4.250 0.5020 0.05206 0.04710 -0.1829 0.6797 0.0563
-4.000 0.5500 0.04597 0.04081 -0.2007 0.6774 0.0608
-3.750 0.5612 0.04515 0.04007 -0.1986 0.6743 0.0625
-3.500 0.6176 0.03968 0.03425 -0.2155 0.6708 0.0713
-3.250 0.6344 0.03844 0.03309 -0.2145 0.6679 0.0735
-3.000 0.6856 0.03506 0.02931 -0.2244 0.6653 0.0849
-2.750 0.7127 0.03381 0.02804 -0.2255 0.6631 0.0921
-2.500 0.7550 0.03158 0.02555 -0.2310 0.6611 0.1049
-2.250 0.7897 0.03005 0.02385 -0.2346 0.6585 0.1197
-2.000 0.8557 0.02504 0.01760 -0.2421 0.6559 0.0573
-1.750 0.8917 0.02357 0.01564 -0.2438 0.6532 0.0499
-1.500 0.9232 0.02271 0.01459 -0.2449 0.6509 0.0495
-1.250 0.9546 0.02207 0.01381 -0.2460 0.6489 0.0526
-1.000 0.9862 0.02159 0.01326 -0.2469 0.6471 0.0550
-0.750 1.0188 0.02121 0.01278 -0.2479 0.6454 0.0582
-0.500 1.0516 0.02094 0.01251 -0.2493 0.6437 0.0661
-0.250 1.0757 0.02103 0.01272 -0.2493 0.6406 0.0767
0.000 1.1050 0.02093 0.01278 -0.2504 0.6378 0.1240
0.250 1.1348 0.02077 0.01358 -0.2514 0.6354 0.5513
0.500 1.1595 0.02118 0.01397 -0.2508 0.6334 0.5923
0.750 1.1845 0.02155 0.01432 -0.2503 0.6317 0.6252
1.000 1.2097 0.02185 0.01461 -0.2497 0.6302 0.6548
1.250 1.2357 0.02211 0.01486 -0.2493 0.6289 0.6816
1.500 1.2621 0.02251 0.01521 -0.2495 0.6274 0.6945
1.750 1.2764 0.02334 0.01614 -0.2479 0.6245 0.7024
2.000 1.2954 0.02399 0.01683 -0.2470 0.6218 0.7104
2.250 1.3171 0.02452 0.01737 -0.2466 0.6196 0.7174
2.500 1.3412 0.02499 0.01782 -0.2465 0.6178 0.7252
2.750 1.3668 0.02534 0.01817 -0.2467 0.6163 0.7335
3.000 1.3947 0.02565 0.01845 -0.2472 0.6149 0.7410
3.250 1.4234 0.02592 0.01870 -0.2478 0.6137 0.7489
3.500 1.4531 0.02624 0.01899 -0.2486 0.6126 0.7578
3.750 1.4621 0.02760 0.02047 -0.2465 0.6103 0.7672
4.000 1.4061 0.03228 0.02550 -0.2353 0.6033 0.7743
4.500 1.4318 0.03417 0.02752 -0.2320 0.5994 0.8070
4.750 1.4545 0.03407 0.02757 -0.2312 0.5982 0.9385
5.000 1.4934 0.03401 0.02746 -0.2334 0.5974 1.0000
5.250 1.5345 0.03384 0.02723 -0.2359 0.5966 1.0000
5.500 1.5748 0.03373 0.02705 -0.2383 0.5959 1.0000
5.750 1.0461 0.08561 0.08002 -0.1953 0.5372 1.0000
6.000 1.0758 0.08581 0.08015 -0.1957 0.5355 1.0000
6.250 1.1094 0.08547 0.07973 -0.1962 0.5343 1.0000
6.500 1.0945 0.09004 0.08434 -0.1946 0.5237 1.0000
6.750 1.1182 0.09061 0.08487 -0.1946 0.5209 1.0000
7.000 1.1455 0.09084 0.08506 -0.1946 0.5193 1.0000
7.250 1.1744 0.09084 0.08502 -0.1947 0.5182 1.0000
7.500 1.1535 0.09646 0.09071 -0.1932 0.5073 1.0000
7.750 1.1782 0.09678 0.09100 -0.1931 0.5049 1.0000
8.000 1.2065 0.09666 0.09088 -0.1930 0.5035 1.0000
8.250 1.2356 0.09648 0.09068 -0.1929 0.5024 1.0000
8.500 1.2655 0.09622 0.09042 -0.1929 0.5017 1.0000
8.750 1.2956 0.09593 0.09015 -0.1928 0.5010 1.0000
9.000 1.2664 0.10244 0.09672 -0.1913 0.4877 1.0000
9.250 1.2966 0.10192 0.09623 -0.1911 0.4868 1.0000
9.500 1.3273 0.10133 0.09565 -0.1910 0.4861 1.0000
9.750 1.3585 0.10066 0.09500 -0.1908 0.4855 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 72-MS-150B AIRFOIL (fx72150b-il)