FX 63-137 13.7% smoothed (fx63137sm-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 63-137 13.7% smoothed (fx63137sm-il) Reynolds number: 50,000 Max Cl/Cd: 31.55 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx63137sm-il-50000-n5.txt Download as CSV file: xf-fx63137sm-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 63-137 13.7% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2265 0.11224 0.10581 -0.0522 0.9710 0.0905
-8.000 -0.2215 0.10587 0.09941 -0.0579 0.9642 0.0687
-7.500 -0.2216 0.09657 0.09015 -0.0659 0.9469 0.0610
-7.250 -0.2120 0.09314 0.08674 -0.0680 0.9397 0.0599
-7.000 -0.2107 0.08987 0.08349 -0.0696 0.9306 0.0590
-6.750 -0.2036 0.08548 0.07912 -0.0737 0.9235 0.0579
-6.500 -0.2050 0.08111 0.07477 -0.0770 0.9130 0.0568
-6.000 -0.1898 0.05944 0.05237 -0.1096 0.8936 0.0526
-5.750 -0.1629 0.05455 0.04716 -0.1167 0.8876 0.0533
-5.500 -0.1383 0.05188 0.04432 -0.1200 0.8807 0.0551
-5.250 -0.0949 0.04749 0.03940 -0.1281 0.8768 0.0574
-5.000 -0.0445 0.04325 0.03445 -0.1361 0.8742 0.0591
-4.750 -0.0149 0.04092 0.03160 -0.1386 0.8666 0.0605
-4.500 0.0237 0.03893 0.02930 -0.1419 0.8621 0.0638
-4.250 0.0642 0.03736 0.02750 -0.1448 0.8587 0.0687
-4.000 0.0925 0.03626 0.02603 -0.1452 0.8520 0.0721
-3.750 0.1227 0.03532 0.02514 -0.1461 0.8461 0.0777
-3.500 0.1603 0.03425 0.02390 -0.1478 0.8423 0.0860
-3.250 0.1903 0.03358 0.02314 -0.1486 0.8363 0.0965
-3.000 0.2230 0.03286 0.02244 -0.1502 0.8298 0.1129
-2.750 0.2741 0.03142 0.02126 -0.1557 0.8264 0.1614
-2.500 0.3310 0.03014 0.02113 -0.1623 0.8241 0.3831
-2.250 0.3494 0.03089 0.02194 -0.1605 0.8149 0.4585
-2.000 0.3777 0.03134 0.02234 -0.1595 0.8092 0.5115
-1.750 0.4074 0.03162 0.02253 -0.1584 0.8051 0.5502
-1.500 0.4174 0.03236 0.02326 -0.1551 0.7946 0.5747
-1.250 0.4489 0.03242 0.02319 -0.1548 0.7902 0.6019
-1.000 0.4670 0.03290 0.02357 -0.1533 0.7812 0.6187
-0.750 0.4986 0.03293 0.02344 -0.1538 0.7754 0.6351
-0.500 0.5387 0.03269 0.02302 -0.1555 0.7718 0.6509
-0.250 0.5495 0.03334 0.02365 -0.1531 0.7610 0.6611
0.000 0.5862 0.03318 0.02336 -0.1543 0.7565 0.6750
0.250 0.6087 0.03362 0.02371 -0.1540 0.7480 0.6878
0.500 0.6385 0.03370 0.02371 -0.1543 0.7415 0.7008
0.750 0.6770 0.03340 0.02332 -0.1556 0.7377 0.7142
1.000 0.6882 0.03421 0.02413 -0.1536 0.7265 0.7258
1.250 0.7256 0.03398 0.02382 -0.1548 0.7221 0.7403
1.500 0.7415 0.03469 0.02453 -0.1535 0.7120 0.7538
1.750 0.7729 0.03458 0.02439 -0.1538 0.7063 0.7683
2.250 0.8174 0.03516 0.02498 -0.1521 0.6906 0.7989
2.500 0.8560 0.03467 0.02447 -0.1532 0.6867 0.8177
2.750 0.8609 0.03572 0.02558 -0.1503 0.6747 0.8355
3.000 0.8945 0.03515 0.02503 -0.1504 0.6704 0.8581
3.250 0.8972 0.03615 0.02613 -0.1472 0.6586 0.8842
3.500 0.9276 0.03547 0.02547 -0.1467 0.6539 0.9345
4.000 0.9931 0.03627 0.02624 -0.1497 0.6373 1.0000
4.250 1.0096 0.03761 0.02760 -0.1494 0.6256 1.0000
4.500 1.0558 0.03714 0.02709 -0.1519 0.6207 1.0000
4.750 1.0692 0.03853 0.02851 -0.1509 0.6088 1.0000
5.000 1.1144 0.03796 0.02794 -0.1530 0.6038 1.0000
5.250 1.1244 0.03945 0.02947 -0.1515 0.5916 1.0000
5.500 1.1705 0.03870 0.02871 -0.1533 0.5866 1.0000
5.750 1.1769 0.04035 0.03044 -0.1513 0.5741 1.0000
6.000 1.2255 0.03935 0.02945 -0.1533 0.5692 1.0000
6.250 1.2282 0.04116 0.03134 -0.1508 0.5563 1.0000
6.500 1.2463 0.04204 0.03229 -0.1499 0.5462 1.0000
6.750 1.2796 0.04184 0.03216 -0.1501 0.5382 1.0000
7.000 1.2873 0.04339 0.03379 -0.1482 0.5263 1.0000
7.250 1.3331 0.04225 0.03269 -0.1494 0.5199 1.0000
7.500 1.3337 0.04422 0.03480 -0.1468 0.5069 1.0000
7.750 1.3500 0.04511 0.03578 -0.1455 0.4961 1.0000
8.000 1.3882 0.04426 0.03498 -0.1458 0.4871 1.0000
8.250 1.3911 0.04599 0.03683 -0.1434 0.4736 1.0000
8.500 1.4029 0.04694 0.03785 -0.1416 0.4601 1.0000
8.750 1.4192 0.04740 0.03837 -0.1400 0.4459 1.0000
9.000 1.4347 0.04791 0.03891 -0.1383 0.4312 1.0000
9.250 1.4481 0.04864 0.03970 -0.1366 0.4162 1.0000
9.500 1.4606 0.04952 0.04061 -0.1350 0.4013 1.0000
9.750 1.4728 0.05051 0.04163 -0.1334 0.3867 1.0000
10.000 1.4762 0.05243 0.04365 -0.1316 0.3718 1.0000
10.250 1.4788 0.05454 0.04586 -0.1300 0.3569 1.0000
10.500 1.4820 0.05666 0.04806 -0.1285 0.3418 1.0000
10.750 1.4851 0.05885 0.05032 -0.1271 0.3265 1.0000
11.000 1.4880 0.06114 0.05268 -0.1258 0.3113 1.0000
11.250 1.4903 0.06356 0.05514 -0.1246 0.2959 1.0000
11.500 1.4918 0.06615 0.05777 -0.1236 0.2805 1.0000
11.750 1.4925 0.06890 0.06057 -0.1226 0.2652 1.0000
12.000 1.4933 0.07176 0.06345 -0.1218 0.2506 1.0000
12.250 1.4938 0.07474 0.06644 -0.1211 0.2365 1.0000
12.500 1.4948 0.07772 0.06941 -0.1205 0.2234 1.0000
12.750 1.4975 0.08051 0.07214 -0.1199 0.2116 1.0000
13.000 1.4960 0.08417 0.07592 -0.1198 0.2003 1.0000
13.250 1.4974 0.08746 0.07926 -0.1196 0.1907 1.0000
13.500 1.5039 0.08985 0.08158 -0.1192 0.1824 1.0000
13.750 1.5019 0.09391 0.08583 -0.1195 0.1743 1.0000
14.250 1.5084 0.10031 0.09240 -0.1198 0.1612 1.0000
14.500 1.5155 0.10290 0.09504 -0.1198 0.1558 1.0000
14.750 1.5217 0.10573 0.09795 -0.1199 0.1510 1.0000
15.000 1.5177 0.11043 0.10292 -0.1211 0.1466 1.0000
15.250 1.5231 0.11337 0.10595 -0.1215 0.1423 1.0000
15.500 1.5364 0.11495 0.10752 -0.1212 0.1384 1.0000
15.750 1.5199 0.12207 0.11501 -0.1241 0.1353 1.0000
16.000 1.5062 0.12894 0.12215 -0.1270 0.1325 1.0000
16.250 1.4974 0.13494 0.12835 -0.1297 0.1298 1.0000
16.500 1.5117 0.13618 0.12964 -0.1295 0.1269 1.0000
16.750 1.5031 0.14226 0.13588 -0.1325 0.1246 1.0000
17.000 1.3442 0.18909 0.18298 -0.1639 0.1198 1.0000
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Polar data table (+)
Polar graphs
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