EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 100,000 Max Cl/Cd: 32.11 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stf86361-il-100000.txt Download as CSV file: xf-stf86361-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5305 0.10749 0.10376 -0.0310 1.0019 0.1166
-8.250 -0.5138 0.10562 0.10189 -0.0270 1.0019 0.1254
-8.000 -0.5413 0.10076 0.09708 -0.0282 1.0019 0.1266
-7.750 -0.5697 0.09623 0.09261 -0.0282 1.0019 0.1266
-7.500 -0.6569 0.09031 0.08640 -0.0325 1.0019 0.1124
-7.250 -0.6823 0.08459 0.08030 -0.0387 1.0019 0.1168
-7.000 -0.6697 0.08159 0.07753 -0.0350 1.0019 0.1235
-6.750 -0.6709 0.07705 0.07286 -0.0368 1.0019 0.1325
-6.500 -0.6666 0.07310 0.06880 -0.0380 1.0019 0.1446
-6.250 -0.6586 0.06973 0.06537 -0.0382 1.0019 0.1596
-6.000 -0.6486 0.06665 0.06224 -0.0383 1.0019 0.1784
-5.750 -0.6394 0.06343 0.05900 -0.0386 1.0019 0.2073
-5.500 -0.6308 0.06121 0.05688 -0.0367 1.0019 0.2439
-4.500 -0.4555 0.04028 0.03190 -0.0529 1.0019 0.0804
-4.250 -0.4246 0.03815 0.02915 -0.0522 1.0019 0.0674
-4.000 -0.3965 0.03668 0.02724 -0.0516 1.0019 0.0618
-3.750 -0.3712 0.03541 0.02589 -0.0511 1.0019 0.0611
-3.500 -0.3459 0.03448 0.02491 -0.0508 1.0019 0.0634
-3.250 -0.3205 0.03379 0.02416 -0.0502 1.0019 0.0633
-3.000 -0.2947 0.03326 0.02365 -0.0498 1.0019 0.0635
-2.750 -0.2677 0.03290 0.02335 -0.0501 1.0019 0.0649
-2.500 -0.2393 0.03275 0.02320 -0.0509 1.0019 0.0689
-2.250 -0.2097 0.03273 0.02316 -0.0522 1.0019 0.0754
-2.000 -0.1791 0.03282 0.02319 -0.0537 1.0019 0.0834
-1.750 -0.1331 0.03289 0.02573 -0.0582 1.0019 0.6570
-1.500 -0.1372 0.03430 0.02725 -0.0499 1.0019 0.7056
-1.250 -0.1397 0.03525 0.02826 -0.0420 1.0019 0.7386
-1.000 -0.1382 0.03598 0.02898 -0.0355 1.0019 0.7687
-0.750 -0.1280 0.03660 0.02954 -0.0315 1.0005 0.7881
-0.500 -0.1110 0.03754 0.03040 -0.0286 0.9973 0.8090
-0.250 -0.0985 0.03807 0.03085 -0.0253 0.9930 0.8297
0.000 -0.0741 0.03911 0.03179 -0.0247 0.9895 0.8453
0.250 -0.0593 0.03936 0.03198 -0.0226 0.9834 0.8604
0.500 -0.0457 0.03967 0.03225 -0.0199 0.9767 0.8778
0.750 -0.0330 0.03992 0.03246 -0.0171 0.9694 0.8957
1.000 0.0030 0.04127 0.03367 -0.0200 0.9642 0.9040
1.250 0.0287 0.04161 0.03395 -0.0215 0.9563 0.9043
1.500 0.0542 0.04220 0.03450 -0.0229 0.9495 0.9053
1.750 0.0973 0.04382 0.03606 -0.0275 0.9435 0.9064
2.000 0.1198 0.04402 0.03624 -0.0283 0.9341 0.9068
2.250 0.1459 0.04472 0.03693 -0.0299 0.9261 0.9072
2.500 0.1902 0.04629 0.03848 -0.0347 0.9187 0.9079
2.750 0.2256 0.04696 0.03915 -0.0374 0.9050 0.9090
3.000 0.2785 0.04589 0.03806 -0.0411 0.8652 0.9100
3.250 0.3148 0.04619 0.03839 -0.0436 0.8513 0.9107
3.500 0.3632 0.04694 0.03921 -0.0482 0.8445 0.9113
3.750 0.3843 0.04714 0.03946 -0.0485 0.8319 0.9120
4.000 0.4163 0.04753 0.03993 -0.0504 0.8213 0.9128
4.250 0.4604 0.04779 0.04027 -0.0540 0.8130 0.9140
4.500 0.4887 0.04780 0.04038 -0.0550 0.7998 0.9155
4.750 0.5220 0.04782 0.04056 -0.0568 0.7881 0.9170
5.000 0.5691 0.04778 0.04067 -0.0605 0.7814 0.9182
5.250 0.5942 0.04796 0.04099 -0.0612 0.7690 0.9191
5.750 0.6721 0.04730 0.04074 -0.0656 0.7509 0.9217
6.000 0.7007 0.04695 0.04059 -0.0661 0.7378 0.9233
6.250 0.7359 0.04624 0.04011 -0.0672 0.7263 0.9250
6.500 0.7917 0.04399 0.03821 -0.0701 0.7182 0.9271
6.750 0.8805 0.03340 0.02801 -0.0696 0.6826 0.9301
7.000 0.9108 0.02996 0.02474 -0.0664 0.6279 0.9333
7.250 0.9212 0.02869 0.02072 -0.0588 0.2102 0.9353
7.500 0.9107 0.03170 0.02255 -0.0541 0.0885 0.9376
7.750 0.9175 0.03335 0.02413 -0.0516 0.0721 0.9405
8.000 0.9262 0.03489 0.02571 -0.0495 0.0651 0.9437
8.250 0.9367 0.03640 0.02724 -0.0477 0.0608 0.9474
8.500 0.9550 0.03781 0.02853 -0.0467 0.0569 0.9517
8.750 0.9863 0.03899 0.02965 -0.0472 0.0514 0.9576
9.000 1.0398 0.04037 0.03112 -0.0500 0.0478 0.9663
9.250 1.1426 0.04433 0.03534 -0.0595 0.0461 0.9804
9.500 1.1720 0.04727 0.03881 -0.0600 0.0438 0.9981
9.750 1.2035 0.05145 0.04359 -0.0606 0.0440 0.9981
10.000 1.2450 0.05738 0.04999 -0.0628 0.0469 0.9981
10.250 1.2368 0.06175 0.05522 -0.0571 0.0527 0.9981
10.500 1.0857 0.07463 0.07082 -0.0294 0.1562 0.9981
10.750 1.0499 0.07852 0.07493 -0.0251 0.1565 0.9981
11.000 1.0144 0.08302 0.07959 -0.0217 0.1565 0.9981
11.250 0.9803 0.08798 0.08468 -0.0194 0.1563 0.9981
11.500 0.9453 0.09342 0.09024 -0.0180 0.1560 0.9981
11.750 0.9071 0.09934 0.09625 -0.0176 0.1557 0.9981
12.000 0.8636 0.10595 0.10294 -0.0185 0.1555 0.9981
12.250 0.8164 0.11362 0.11064 -0.0212 0.1553 0.9981
12.500 0.7765 0.12199 0.11897 -0.0252 0.1536 0.9981
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Polar data table (+)
Polar graphs
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