EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 50,000 Max Cl/Cd: 23.75 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stf86361-il-50000-n5.txt Download as CSV file: xf-stf86361-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER STF 863-615 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5220 0.12950 0.12346 -0.0281 1.0019 0.1589
-9.500 -0.5230 0.12623 0.12022 -0.0273 1.0019 0.1617
-9.000 -0.4919 0.09855 0.09289 -0.0463 0.9960 0.0561
-8.750 -0.5284 0.09421 0.08850 -0.0474 0.9939 0.0565
-8.250 -0.6159 0.09436 0.08844 -0.0421 0.9983 0.0608
-7.750 -0.6291 0.08382 0.07750 -0.0471 0.9937 0.0533
-7.500 -0.6272 0.07902 0.07252 -0.0486 0.9915 0.0513
-7.250 -0.6217 0.07392 0.06711 -0.0507 0.9893 0.0489
-7.000 -0.6089 0.06791 0.06035 -0.0540 0.9870 0.0453
-6.750 -0.5888 0.06418 0.05597 -0.0557 0.9846 0.0433
-6.500 -0.5698 0.06025 0.05173 -0.0568 0.9825 0.0425
-6.250 -0.5470 0.05664 0.04772 -0.0582 0.9805 0.0419
-6.000 -0.5207 0.05342 0.04403 -0.0597 0.9785 0.0414
-5.750 -0.4911 0.05079 0.04084 -0.0612 0.9765 0.0421
-5.500 -0.4586 0.04890 0.03828 -0.0627 0.9746 0.0437
-5.250 -0.4320 0.04652 0.03563 -0.0631 0.9725 0.0446
-5.000 -0.4064 0.04477 0.03356 -0.0627 0.9701 0.0449
-4.750 -0.3811 0.04336 0.03197 -0.0620 0.9678 0.0455
-4.500 -0.3565 0.04240 0.03089 -0.0607 0.9656 0.0463
-4.250 -0.3320 0.04180 0.03019 -0.0595 0.9634 0.0488
-4.000 -0.3050 0.04147 0.02969 -0.0591 0.9613 0.0529
-3.750 -0.2843 0.04088 0.02893 -0.0577 0.9579 0.0551
-3.500 -0.2593 0.04034 0.02819 -0.0575 0.9548 0.0568
-3.250 -0.2299 0.03969 0.02741 -0.0589 0.9521 0.0602
-3.000 -0.1967 0.03934 0.02689 -0.0610 0.9495 0.0654
-2.750 -0.1627 0.03894 0.02644 -0.0635 0.9466 0.0787
-2.250 -0.1222 0.03920 0.02926 -0.0599 0.9390 0.6905
-2.000 -0.1076 0.04031 0.03022 -0.0554 0.9351 0.7305
-1.750 -0.1016 0.04054 0.03036 -0.0500 0.9294 0.7512
-1.500 -0.0779 0.04087 0.03044 -0.0494 0.9251 0.7628
-1.250 -0.0596 0.04135 0.03077 -0.0467 0.9212 0.7864
-1.000 -0.0545 0.04128 0.03062 -0.0416 0.9152 0.8058
-0.750 -0.0373 0.04144 0.03066 -0.0393 0.9109 0.8226
-0.500 -0.0215 0.04154 0.03064 -0.0368 0.9064 0.8398
-0.250 -0.0022 0.04160 0.03058 -0.0359 0.9010 0.8481
0.000 0.0298 0.04196 0.03075 -0.0379 0.8970 0.8499
0.250 0.0575 0.04227 0.03093 -0.0392 0.8924 0.8517
0.500 0.0836 0.04255 0.03112 -0.0403 0.8871 0.8535
0.750 0.1172 0.04302 0.03148 -0.0427 0.8830 0.8549
1.000 0.1434 0.04338 0.03176 -0.0438 0.8776 0.8565
1.250 0.1717 0.04381 0.03213 -0.0454 0.8723 0.8581
1.500 0.2056 0.04431 0.03260 -0.0477 0.8683 0.8595
1.750 0.2264 0.04460 0.03289 -0.0478 0.8611 0.8607
2.000 0.2595 0.04503 0.03331 -0.0499 0.8555 0.8621
2.250 0.2845 0.04528 0.03357 -0.0505 0.8470 0.8637
2.500 0.3202 0.04566 0.03398 -0.0530 0.8409 0.8654
2.750 0.3431 0.04596 0.03434 -0.0533 0.8321 0.8670
3.000 0.3786 0.04640 0.03484 -0.0558 0.8269 0.8683
3.250 0.3999 0.04679 0.03531 -0.0560 0.8183 0.8696
3.500 0.4349 0.04725 0.03586 -0.0584 0.8132 0.8712
3.750 0.4550 0.04767 0.03642 -0.0585 0.8042 0.8730
4.000 0.4892 0.04803 0.03691 -0.0605 0.7992 0.8749
4.250 0.5074 0.04845 0.03747 -0.0601 0.7895 0.8768
4.500 0.5349 0.04884 0.03807 -0.0612 0.7823 0.8787
4.750 0.5625 0.04923 0.03863 -0.0622 0.7745 0.8804
5.000 0.5849 0.04966 0.03924 -0.0626 0.7648 0.8822
5.250 0.6152 0.04981 0.03961 -0.0638 0.7557 0.8841
5.500 0.6497 0.04967 0.03975 -0.0654 0.7463 0.8863
5.750 0.6733 0.04964 0.03997 -0.0652 0.7339 0.8888
6.000 0.6963 0.04973 0.04032 -0.0651 0.7217 0.8915
6.250 0.7209 0.04979 0.04066 -0.0652 0.7094 0.8945
6.500 0.7478 0.04967 0.04085 -0.0654 0.6967 0.8976
6.750 0.7758 0.04937 0.04095 -0.0655 0.6827 0.9007
7.000 0.8033 0.04881 0.04076 -0.0652 0.6676 0.9040
7.250 0.8335 0.04787 0.04024 -0.0648 0.6512 0.9076
7.500 0.8700 0.04432 0.03713 -0.0623 0.6177 0.9119
7.750 0.9035 0.03805 0.02945 -0.0542 0.3446 0.9162
8.000 0.8946 0.04056 0.03091 -0.0500 0.2066 0.9207
8.250 0.8883 0.04347 0.03305 -0.0470 0.1113 0.9262
8.500 0.8901 0.04583 0.03513 -0.0447 0.0795 0.9335
8.750 0.8960 0.04774 0.03707 -0.0428 0.0677 0.9454
9.000 0.9005 0.04923 0.03868 -0.0406 0.0613 0.9960
9.250 0.9134 0.05121 0.04076 -0.0401 0.0545 0.9981
9.500 0.9297 0.05296 0.04269 -0.0394 0.0494 0.9981
9.750 0.9544 0.05431 0.04430 -0.0391 0.0460 0.9981
10.000 0.9962 0.05530 0.04542 -0.0399 0.0427 0.9981
10.250 1.0627 0.05715 0.04753 -0.0430 0.0395 0.9981
10.500 1.0931 0.05980 0.05070 -0.0436 0.0365 0.9981
10.750 1.1164 0.06294 0.05424 -0.0438 0.0346 0.9981
11.000 1.1319 0.06656 0.05828 -0.0432 0.0339 0.9981
11.250 1.1376 0.07030 0.06242 -0.0419 0.0335 0.9981
11.500 1.1361 0.07414 0.06665 -0.0401 0.0333 0.9981
11.750 1.1291 0.07811 0.07098 -0.0382 0.0331 0.9981
12.000 1.1174 0.08227 0.07548 -0.0364 0.0331 0.9981
12.250 1.1021 0.08666 0.08020 -0.0349 0.0332 0.9981
12.500 1.0842 0.09133 0.08516 -0.0338 0.0332 0.9981
12.750 1.0638 0.09640 0.09051 -0.0335 0.0334 0.9981
13.000 1.0416 0.10202 0.09640 -0.0341 0.0336 0.9981
13.250 1.0182 0.10835 0.10296 -0.0359 0.0340 0.9981
13.500 0.9943 0.11557 0.11038 -0.0391 0.0344 0.9981
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Polar data table (+)
Polar graphs
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