EPPLER STF 863-615 AIRFOIL (stf86361-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER STF 863-615 AIRFOIL (stf86361-il) Reynolds number: 200,000 Max Cl/Cd: 56.33 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-stf86361-il-200000-n5.txt Download as CSV file: xf-stf86361-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.0763 0.11188 0.10785 -0.1298 0.9308 0.0198
-13.750 -0.0796 0.10801 0.10399 -0.1317 0.9297 0.0201
-13.500 -0.0811 0.10418 0.10017 -0.1333 0.9286 0.0201
-13.250 -0.0828 0.10010 0.09610 -0.1349 0.9276 0.0202
-13.000 -0.0734 0.09826 0.09426 -0.1334 0.9267 0.0213
-12.750 -0.0708 0.09507 0.09107 -0.1342 0.9257 0.0218
-12.500 -0.0699 0.09137 0.08738 -0.1354 0.9248 0.0221
-12.250 -0.0701 0.08743 0.08345 -0.1366 0.9240 0.0225
-12.000 -0.0712 0.08327 0.07929 -0.1381 0.9233 0.0227
-11.750 -0.0732 0.07883 0.07486 -0.1397 0.9226 0.0229
-11.500 -0.0765 0.07402 0.07006 -0.1416 0.9220 0.0230
-8.500 -0.3579 0.05030 0.04515 -0.1206 0.8865 0.0144
-8.250 -0.3542 0.04749 0.04218 -0.1193 0.8847 0.0141
-8.000 -0.3432 0.04439 0.03879 -0.1191 0.8834 0.0138
-7.750 -0.3260 0.04117 0.03522 -0.1194 0.8824 0.0137
-7.250 -0.3249 0.03806 0.03162 -0.1118 0.8755 0.0137
-7.000 -0.3066 0.03587 0.02903 -0.1110 0.8736 0.0139
-6.750 -0.2837 0.03408 0.02680 -0.1107 0.8724 0.0143
-6.500 -0.2600 0.03230 0.02483 -0.1110 0.8715 0.0158
-6.250 -0.2338 0.03112 0.02350 -0.1116 0.8706 0.0173
-6.000 -0.2053 0.02974 0.02188 -0.1120 0.8698 0.0180
-5.750 -0.1765 0.02857 0.02050 -0.1123 0.8692 0.0184
-5.500 -0.1479 0.02764 0.01941 -0.1126 0.8686 0.0191
-5.250 -0.1182 0.02721 0.01876 -0.1132 0.8681 0.0202
-5.000 -0.1126 0.02649 0.01818 -0.1097 0.8640 0.0216
-4.750 -0.0930 0.02598 0.01767 -0.1088 0.8616 0.0227
-4.500 -0.0671 0.02543 0.01709 -0.1091 0.8600 0.0233
-4.250 -0.0377 0.02487 0.01650 -0.1102 0.8586 0.0240
-4.000 -0.0063 0.02439 0.01597 -0.1117 0.8575 0.0249
-3.750 0.0261 0.02401 0.01548 -0.1135 0.8566 0.0269
-3.500 0.0600 0.02363 0.01500 -0.1155 0.8558 0.0284
-3.250 0.0936 0.02340 0.01467 -0.1172 0.8550 0.0294
-3.000 0.1271 0.02323 0.01442 -0.1188 0.8544 0.0309
-2.750 0.1395 0.02357 0.01470 -0.1167 0.8493 0.0323
-2.500 0.1646 0.02362 0.01474 -0.1168 0.8466 0.0367
-2.250 0.2133 0.02236 0.01564 -0.1235 0.8466 0.6234
-2.000 0.2398 0.02266 0.01585 -0.1234 0.8445 0.6381
-1.750 0.2691 0.02284 0.01595 -0.1238 0.8428 0.6484
-1.500 0.2986 0.02306 0.01615 -0.1239 0.8414 0.6621
-1.250 0.3303 0.02312 0.01617 -0.1245 0.8404 0.6697
-1.000 0.3402 0.02362 0.01664 -0.1218 0.8329 0.6743
-0.750 0.3619 0.02400 0.01705 -0.1204 0.8303 0.6859
-0.500 0.3854 0.02438 0.01749 -0.1190 0.8286 0.7018
-0.250 0.4151 0.02435 0.01747 -0.1196 0.8274 0.7039
0.000 0.4475 0.02426 0.01737 -0.1208 0.8264 0.7049
0.500 0.4859 0.02472 0.01783 -0.1188 0.8160 0.7066
0.750 0.5186 0.02456 0.01768 -0.1201 0.8144 0.7076
1.000 0.5520 0.02437 0.01751 -0.1215 0.8131 0.7087
1.250 0.5860 0.02417 0.01733 -0.1230 0.8121 0.7096
1.500 0.5938 0.02472 0.01791 -0.1201 0.8024 0.7106
1.750 0.6257 0.02458 0.01783 -0.1213 0.8007 0.7113
2.000 0.6589 0.02439 0.01769 -0.1226 0.7995 0.7122
2.500 0.7014 0.02471 0.01811 -0.1214 0.7879 0.7145
2.750 0.7349 0.02444 0.01793 -0.1227 0.7863 0.7153
3.250 0.7806 0.02446 0.01812 -0.1217 0.7740 0.7167
4.750 0.9891 0.01756 0.01078 -0.1245 0.5478 0.7210
5.000 0.9729 0.01943 0.01190 -0.1171 0.4297 0.7219
5.250 0.9571 0.02159 0.01333 -0.1104 0.3040 0.7227
5.500 0.9495 0.02364 0.01465 -0.1054 0.1796 0.7234
5.750 0.9514 0.02528 0.01577 -0.1020 0.0882 0.7242
6.000 0.9596 0.02659 0.01679 -0.0996 0.0376 0.7249
6.250 0.9748 0.02743 0.01764 -0.0980 0.0277 0.7258
6.500 0.9908 0.02822 0.01851 -0.0967 0.0242 0.7266
6.750 1.0055 0.02913 0.01951 -0.0951 0.0222 0.7274
7.000 1.0205 0.03001 0.02051 -0.0936 0.0212 0.7283
7.250 1.0355 0.03091 0.02153 -0.0921 0.0200 0.7291
7.500 1.0496 0.03186 0.02258 -0.0906 0.0186 0.7299
7.750 1.0622 0.03291 0.02373 -0.0889 0.0177 0.7308
8.000 1.0736 0.03408 0.02503 -0.0870 0.0170 0.7316
8.250 1.0842 0.03533 0.02638 -0.0851 0.0164 0.7325
8.500 1.0943 0.03671 0.02785 -0.0830 0.0159 0.7334
8.750 1.1044 0.03827 0.02950 -0.0809 0.0153 0.7343
9.000 1.1191 0.03979 0.03112 -0.0794 0.0147 0.7352
9.250 1.1357 0.04083 0.03232 -0.0782 0.0139 0.7361
9.500 1.1531 0.04205 0.03370 -0.0771 0.0131 0.7370
9.750 1.1728 0.04346 0.03528 -0.0762 0.0126 0.7380
10.000 1.1928 0.04503 0.03703 -0.0754 0.0120 0.7390
10.250 1.2117 0.04679 0.03900 -0.0745 0.0115 0.7401
10.500 1.2256 0.04857 0.04098 -0.0732 0.0110 0.7412
10.750 1.2351 0.05037 0.04294 -0.0716 0.0104 0.7422
11.000 1.2468 0.05399 0.04677 -0.0704 0.0095 0.7432
11.250 1.2469 0.05591 0.04900 -0.0677 0.0092 0.7442
11.500 1.2465 0.05850 0.05193 -0.0651 0.0090 0.7451
11.750 1.2429 0.06156 0.05533 -0.0624 0.0088 0.7459
12.000 1.2356 0.06491 0.05902 -0.0596 0.0086 0.7468
12.250 1.2248 0.06861 0.06304 -0.0568 0.0085 0.7476
12.500 1.2111 0.07259 0.06733 -0.0543 0.0084 0.7484
12.750 1.1957 0.07685 0.07188 -0.0522 0.0084 0.7492
13.000 1.1781 0.08151 0.07682 -0.0506 0.0083 0.7500
13.250 1.1593 0.08660 0.08216 -0.0497 0.0083 0.7508
13.500 1.1403 0.09202 0.08782 -0.0497 0.0083 0.7516
13.750 1.1194 0.09819 0.09423 -0.0505 0.0083 0.7524
14.000 1.0982 0.10497 0.10124 -0.0525 0.0083 0.7532
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Polar data table (+)
Polar graphs
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