WORTMANN FX 63-137 AIRFOIL (fx63137-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: WORTMANN FX 63-137 AIRFOIL (fx63137-il) Reynolds number: 200,000 Max Cl/Cd: 85.17 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137-il-200000-n5.txt Download as CSV file: xf-fx63137-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 63-137 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2513 0.06200 0.05840 -0.1032 0.9344 0.0184
-9.500 -0.3218 0.03337 0.02864 -0.1426 0.9066 0.0181
-9.250 -0.2866 0.03087 0.02595 -0.1500 0.9007 0.0189
-9.000 -0.2465 0.02887 0.02372 -0.1566 0.8968 0.0202
-8.750 -0.2162 0.02648 0.02091 -0.1614 0.8885 0.0220
-8.500 -0.1777 0.02628 0.02072 -0.1646 0.8835 0.0233
-8.250 -0.1405 0.02431 0.01829 -0.1692 0.8779 0.0251
-8.000 -0.1092 0.02340 0.01725 -0.1712 0.8702 0.0258
-7.750 -0.0731 0.02246 0.01614 -0.1740 0.8647 0.0265
-7.500 -0.0423 0.02153 0.01502 -0.1757 0.8580 0.0272
-7.250 -0.0102 0.02058 0.01385 -0.1774 0.8516 0.0281
-7.000 0.0248 0.01964 0.01261 -0.1795 0.8466 0.0293
-6.750 0.0531 0.01915 0.01208 -0.1802 0.8399 0.0301
-6.500 0.0845 0.01861 0.01142 -0.1814 0.8342 0.0310
-6.250 0.1176 0.01806 0.01071 -0.1828 0.8290 0.0324
-6.000 0.1454 0.01757 0.01006 -0.1831 0.8214 0.0337
-5.750 0.1766 0.01705 0.00950 -0.1842 0.8150 0.0349
-5.500 0.2063 0.01658 0.00896 -0.1848 0.8087 0.0359
-5.250 0.2360 0.01612 0.00843 -0.1855 0.8025 0.0369
-5.000 0.2680 0.01567 0.00789 -0.1865 0.7975 0.0380
-4.750 0.2983 0.01529 0.00741 -0.1873 0.7919 0.0390
-4.500 0.3298 0.01481 0.00692 -0.1884 0.7858 0.0402
-4.250 0.3631 0.01443 0.00647 -0.1898 0.7804 0.0420
-4.000 0.3941 0.01412 0.00609 -0.1907 0.7743 0.0446
-3.750 0.4258 0.01382 0.00577 -0.1917 0.7682 0.0485
-3.500 0.4585 0.01359 0.00549 -0.1929 0.7631 0.0553
-3.250 0.4885 0.01341 0.00529 -0.1934 0.7568 0.0662
-3.000 0.5205 0.01315 0.00508 -0.1945 0.7508 0.0850
-2.750 0.5532 0.01294 0.00488 -0.1957 0.7455 0.1166
-2.500 0.5853 0.01260 0.00476 -0.1970 0.7386 0.1879
-2.250 0.6201 0.01219 0.00469 -0.1990 0.7325 0.3088
-2.000 0.6513 0.01208 0.00474 -0.1998 0.7265 0.3810
-1.750 0.6804 0.01209 0.00482 -0.2000 0.7198 0.4231
-1.500 0.7099 0.01215 0.00488 -0.2002 0.7142 0.4569
-1.250 0.7381 0.01224 0.00499 -0.2002 0.7078 0.4826
-1.000 0.7663 0.01232 0.00506 -0.2001 0.7007 0.5017
-0.750 0.7947 0.01240 0.00510 -0.2000 0.6943 0.5156
-0.500 0.8222 0.01249 0.00517 -0.1998 0.6864 0.5300
-0.250 0.8506 0.01258 0.00520 -0.1998 0.6795 0.5451
0.000 0.8777 0.01268 0.00530 -0.1995 0.6713 0.5581
0.250 0.9055 0.01277 0.00534 -0.1993 0.6642 0.5673
0.500 0.9328 0.01286 0.00541 -0.1992 0.6557 0.5758
0.750 0.9600 0.01294 0.00547 -0.1989 0.6472 0.5823
1.000 0.9865 0.01303 0.00556 -0.1986 0.6373 0.5897
1.250 1.0136 0.01313 0.00561 -0.1983 0.6279 0.5969
1.500 1.0400 0.01323 0.00571 -0.1979 0.6180 0.6037
1.750 1.0670 0.01336 0.00579 -0.1977 0.6088 0.6117
2.000 1.0933 0.01349 0.00592 -0.1973 0.5995 0.6182
2.250 1.1197 0.01363 0.00605 -0.1970 0.5900 0.6263
2.500 1.1457 0.01379 0.00620 -0.1966 0.5797 0.6333
2.750 1.1710 0.01394 0.00635 -0.1961 0.5667 0.6401
3.000 1.1959 0.01414 0.00648 -0.1955 0.5522 0.6474
3.250 1.2196 0.01436 0.00667 -0.1946 0.5365 0.6536
3.500 1.2432 0.01461 0.00687 -0.1938 0.5194 0.6612
3.750 1.2665 0.01487 0.00710 -0.1929 0.5019 0.6686
4.000 1.2894 0.01517 0.00735 -0.1920 0.4860 0.6772
4.250 1.3122 0.01548 0.00763 -0.1911 0.4719 0.6857
4.500 1.3351 0.01579 0.00793 -0.1902 0.4586 0.6952
4.750 1.3576 0.01610 0.00826 -0.1893 0.4443 0.7046
5.250 1.4008 0.01681 0.00896 -0.1871 0.4183 0.7259
5.500 1.4216 0.01720 0.00936 -0.1859 0.4063 0.7369
5.750 1.4416 0.01761 0.00977 -0.1846 0.3935 0.7493
6.000 1.4608 0.01801 0.01020 -0.1831 0.3785 0.7625
6.250 1.4779 0.01847 0.01067 -0.1812 0.3630 0.7775
6.500 1.4917 0.01901 0.01119 -0.1788 0.3494 0.7947
6.750 1.5049 0.01953 0.01172 -0.1763 0.3343 0.8149
7.000 1.5169 0.02000 0.01225 -0.1735 0.3166 0.8422
7.500 1.5272 0.02128 0.01350 -0.1658 0.2844 1.0000
7.750 1.5403 0.02213 0.01430 -0.1638 0.2662 1.0000
8.000 1.5518 0.02307 0.01520 -0.1617 0.2462 1.0000
8.250 1.5607 0.02420 0.01625 -0.1592 0.2322 1.0000
8.500 1.5709 0.02530 0.01733 -0.1571 0.2207 1.0000
8.750 1.5825 0.02636 0.01841 -0.1552 0.2055 1.0000
9.000 1.5902 0.02771 0.01972 -0.1530 0.1887 1.0000
9.250 1.5964 0.02923 0.02118 -0.1508 0.1767 1.0000
9.500 1.6032 0.03078 0.02272 -0.1487 0.1660 1.0000
9.750 1.6131 0.03214 0.02413 -0.1471 0.1492 1.0000
10.000 1.6167 0.03407 0.02600 -0.1450 0.1360 1.0000
10.250 1.6203 0.03609 0.02798 -0.1432 0.1275 1.0000
10.500 1.6286 0.03775 0.02973 -0.1417 0.1176 1.0000
10.750 1.6345 0.03969 0.03170 -0.1402 0.1056 1.0000
11.000 1.6370 0.04201 0.03401 -0.1387 0.0977 1.0000
11.250 1.6391 0.04446 0.03645 -0.1373 0.0926 1.0000
11.500 1.6431 0.04677 0.03883 -0.1360 0.0880 1.0000
11.750 1.6464 0.04924 0.04138 -0.1349 0.0835 1.0000
12.000 1.6467 0.05211 0.04430 -0.1339 0.0797 1.0000
12.250 1.6538 0.05428 0.04660 -0.1331 0.0759 1.0000
12.500 1.6585 0.05680 0.04920 -0.1324 0.0716 1.0000
12.750 1.6608 0.05965 0.05211 -0.1318 0.0683 1.0000
13.000 1.6638 0.06250 0.05504 -0.1312 0.0659 1.0000
13.250 1.6653 0.06559 0.05818 -0.1309 0.0634 1.0000
13.500 1.6653 0.06897 0.06162 -0.1306 0.0613 1.0000
13.750 1.6649 0.07251 0.06522 -0.1305 0.0592 1.0000
14.000 1.6668 0.07578 0.06862 -0.1304 0.0578 1.0000
14.250 1.6678 0.07924 0.07220 -0.1305 0.0563 1.0000
14.500 1.6676 0.08293 0.07599 -0.1307 0.0548 1.0000
14.750 1.6660 0.08690 0.08007 -0.1311 0.0534 1.0000
15.000 1.6628 0.09119 0.08444 -0.1317 0.0519 1.0000
|
Polar data table (+)
Polar graphs
<< Back to WORTMANN FX 63-137 AIRFOIL (fx63137-il)