EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 500,000 Max Cl/Cd: 92.24 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-stf86361-il-500000.txt Download as CSV file: xf-stf86361-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1372 0.08740 0.08464 -0.1413 0.9285 0.0135
-11.500 -0.1368 0.08236 0.07962 -0.1446 0.9271 0.0137
-11.250 -0.1380 0.07636 0.07364 -0.1490 0.9257 0.0139
-11.000 -0.1421 0.06916 0.06643 -0.1552 0.9241 0.0139
-10.750 -0.1512 0.06325 0.06047 -0.1601 0.9225 0.0138
-10.500 -0.1630 0.05833 0.05545 -0.1636 0.9209 0.0138
-10.250 -0.1756 0.05404 0.05103 -0.1660 0.9188 0.0139
-10.000 -0.1906 0.05059 0.04743 -0.1670 0.9157 0.0140
-9.750 -0.2093 0.04831 0.04493 -0.1660 0.9121 0.0141
-9.500 -0.2227 0.04616 0.04246 -0.1640 0.9094 0.0142
-9.250 -0.2287 0.04408 0.04004 -0.1622 0.9075 0.0142
-8.750 -0.2995 0.04684 0.04296 -0.1391 0.8955 0.0142
-8.500 -0.3036 0.04481 0.04055 -0.1363 0.8937 0.0142
-8.250 -0.2879 0.04089 0.03674 -0.1366 0.8932 0.0144
-8.000 -0.3544 0.04468 0.04037 -0.1184 0.8839 0.0143
-7.750 -0.3409 0.04137 0.03716 -0.1180 0.8824 0.0145
-7.500 -0.3266 0.03922 0.03493 -0.1177 0.8811 0.0147
-7.250 -0.3076 0.03707 0.03261 -0.1180 0.8800 0.0152
-7.000 -0.2816 0.03527 0.03005 -0.1181 0.8790 0.0171
-6.750 -0.2554 0.03182 0.02654 -0.1194 0.8786 0.0177
-6.500 -0.2258 0.03004 0.02462 -0.1208 0.8781 0.0193
-6.250 -0.1925 0.02824 0.02229 -0.1225 0.8776 0.0238
-6.000 -0.1614 0.02664 0.02065 -0.1241 0.8773 0.0276
-5.000 -0.0333 0.02268 0.01606 -0.1267 0.8761 0.0236
-4.750 -0.0619 0.02352 0.01689 -0.1168 0.8659 0.0236
-4.500 -0.0310 0.02288 0.01623 -0.1175 0.8650 0.0235
-4.250 0.0019 0.02188 0.01537 -0.1193 0.8643 0.0245
-4.000 0.0358 0.02141 0.01489 -0.1211 0.8637 0.0261
-3.750 0.0709 0.02098 0.01443 -0.1232 0.8631 0.0266
-3.500 0.1089 0.02043 0.01388 -0.1260 0.8626 0.0275
-3.250 0.1465 0.02003 0.01347 -0.1285 0.8622 0.0292
-3.000 0.1839 0.01971 0.01312 -0.1309 0.8617 0.0313
-2.750 0.2205 0.01947 0.01283 -0.1330 0.8613 0.0338
-2.500 0.2822 0.01755 0.01282 -0.1434 0.8617 0.6166
-2.250 0.3133 0.01781 0.01311 -0.1437 0.8611 0.6412
-2.000 0.3071 0.01880 0.01412 -0.1375 0.8510 0.6494
-1.750 0.3341 0.01901 0.01433 -0.1371 0.8492 0.6607
-1.500 0.3633 0.01922 0.01453 -0.1370 0.8479 0.6719
-1.250 0.3911 0.01932 0.01472 -0.1364 0.8469 0.6813
-1.000 0.4226 0.01934 0.01474 -0.1370 0.8461 0.6884
-0.750 0.4543 0.01930 0.01471 -0.1376 0.8456 0.6953
-0.500 0.4814 0.01936 0.01485 -0.1370 0.8449 0.7019
-0.250 0.5151 0.01920 0.01468 -0.1384 0.8444 0.7040
0.000 0.5498 0.01899 0.01445 -0.1401 0.8439 0.7050
0.250 0.5422 0.02006 0.01552 -0.1344 0.8320 0.7063
0.500 0.5756 0.01990 0.01536 -0.1359 0.8312 0.7074
0.750 0.6100 0.01968 0.01515 -0.1375 0.8306 0.7083
1.000 0.6449 0.01943 0.01492 -0.1393 0.8300 0.7088
1.250 0.6804 0.01911 0.01461 -0.1411 0.8294 0.7094
1.500 0.7172 0.01868 0.01421 -0.1430 0.8290 0.7100
1.750 0.7553 0.01814 0.01370 -0.1452 0.8286 0.7107
2.000 0.7930 0.01759 0.01320 -0.1473 0.8284 0.7113
2.250 0.8299 0.01712 0.01278 -0.1494 0.8281 0.7119
2.500 0.8654 0.01660 0.01233 -0.1511 0.8266 0.7124
2.750 0.9515 0.01393 0.00972 -0.1619 0.8272 0.7128
3.000 0.9412 0.01407 0.00992 -0.1542 0.8153 0.7135
3.250 0.9939 0.01227 0.00816 -0.1585 0.8084 0.7140
3.500 1.0022 0.01191 0.00784 -0.1543 0.7918 0.7147
3.750 1.0048 0.01204 0.00800 -0.1493 0.7651 0.7157
4.000 1.0349 0.01122 0.00656 -0.1488 0.6531 0.7165
4.250 1.0182 0.01266 0.00751 -0.1404 0.5693 0.7171
4.500 1.0014 0.01433 0.00871 -0.1325 0.4763 0.7178
4.750 0.9911 0.01599 0.00989 -0.1263 0.3890 0.7183
5.000 0.9798 0.01793 0.01113 -0.1201 0.2604 0.7189
5.250 0.9717 0.01994 0.01234 -0.1148 0.1189 0.7194
5.500 0.9723 0.02157 0.01345 -0.1108 0.0310 0.7200
5.750 0.9888 0.02224 0.01411 -0.1093 0.0246 0.7206
6.000 1.0060 0.02287 0.01477 -0.1080 0.0218 0.7212
6.250 1.0214 0.02364 0.01556 -0.1065 0.0202 0.7218
6.500 1.0379 0.02432 0.01631 -0.1050 0.0192 0.7224
6.750 1.0528 0.02512 0.01716 -0.1034 0.0182 0.7230
7.000 1.0638 0.02620 0.01825 -0.1012 0.0174 0.7236
7.250 1.0774 0.02711 0.01923 -0.0994 0.0168 0.7244
7.500 1.0914 0.02798 0.02016 -0.0978 0.0157 0.7253
7.750 1.1016 0.02916 0.02134 -0.0956 0.0148 0.7261
8.000 1.1125 0.03036 0.02261 -0.0935 0.0143 0.7267
8.250 1.1271 0.03132 0.02366 -0.0918 0.0138 0.7273
8.500 1.1419 0.03234 0.02475 -0.0903 0.0132 0.7278
8.750 1.1578 0.03340 0.02584 -0.0889 0.0126 0.7283
9.000 1.1845 0.03480 0.02722 -0.0887 0.0119 0.7288
9.250 1.2016 0.03584 0.02849 -0.0872 0.0114 0.7293
9.500 1.2192 0.03688 0.02968 -0.0861 0.0106 0.7301
9.750 1.2394 0.03790 0.03067 -0.0857 0.0099 0.7310
10.000 1.2661 0.03981 0.03281 -0.0857 0.0094 0.7318
10.250 1.2820 0.04163 0.03494 -0.0841 0.0091 0.7326
10.500 1.2954 0.04387 0.03752 -0.0821 0.0088 0.7334
10.750 1.3036 0.04647 0.04046 -0.0797 0.0085 0.7341
11.000 1.3060 0.04887 0.04312 -0.0768 0.0081 0.7349
11.250 1.3069 0.05094 0.04536 -0.0741 0.0079 0.7357
11.500 1.3157 0.05188 0.04621 -0.0729 0.0075 0.7366
12.000 1.2913 0.06009 0.05504 -0.0652 0.0072 0.7379
12.250 1.2717 0.06376 0.05905 -0.0610 0.0071 0.7385
12.500 1.2540 0.06799 0.06353 -0.0576 0.0072 0.7391
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Polar data table (+)
Polar graphs
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