SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 100,000 Max Cl/Cd: 50.71 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6060-il-100000-n5.txt Download as CSV file: xf-sd6060-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6060-104-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5049 0.07254 0.06783 -0.0398 1.0000 0.0190
-8.750 -0.5171 0.06695 0.06222 -0.0437 1.0000 0.0189
-8.500 -0.5301 0.06295 0.05817 -0.0446 1.0000 0.0188
-8.250 -0.5398 0.05892 0.05404 -0.0449 1.0000 0.0187
-8.000 -0.5485 0.05464 0.04957 -0.0447 1.0000 0.0188
-7.750 -0.5550 0.05062 0.04527 -0.0435 1.0000 0.0190
-7.500 -0.5574 0.04731 0.04173 -0.0415 1.0000 0.0189
-7.250 -0.5601 0.04425 0.03838 -0.0388 1.0000 0.0190
-7.000 -0.5615 0.04144 0.03526 -0.0357 1.0000 0.0190
-6.750 -0.5613 0.03882 0.03231 -0.0325 1.0000 0.0191
-6.500 -0.5483 0.03563 0.02866 -0.0315 0.9962 0.0191
-6.250 -0.5210 0.03215 0.02464 -0.0328 0.9883 0.0193
-6.000 -0.4912 0.02906 0.02112 -0.0343 0.9821 0.0197
-5.750 -0.4610 0.02676 0.01848 -0.0354 0.9751 0.0204
-5.500 -0.4265 0.02479 0.01623 -0.0371 0.9702 0.0215
-5.250 -0.3954 0.02329 0.01451 -0.0380 0.9629 0.0236
-5.000 -0.3608 0.02186 0.01287 -0.0394 0.9576 0.0270
-4.750 -0.3322 0.02060 0.01157 -0.0399 0.9496 0.0303
-4.500 -0.2997 0.01945 0.01021 -0.0409 0.9435 0.0353
-4.250 -0.2728 0.01845 0.00916 -0.0409 0.9345 0.0478
-4.000 -0.2434 0.01742 0.00832 -0.0415 0.9276 0.0801
-3.750 -0.2179 0.01652 0.00770 -0.0415 0.9185 0.1397
-3.500 -0.1929 0.01561 0.00722 -0.0414 0.9102 0.2354
-3.250 -0.1690 0.01464 0.00683 -0.0410 0.9023 0.3806
-3.000 -0.1492 0.01386 0.00671 -0.0393 0.8929 0.5444
-2.750 -0.1237 0.01351 0.00674 -0.0378 0.8865 0.6746
-2.500 -0.0998 0.01348 0.00680 -0.0360 0.8773 0.7503
-2.250 -0.0724 0.01351 0.00678 -0.0349 0.8702 0.8011
-2.000 -0.0447 0.01358 0.00675 -0.0340 0.8620 0.8386
-1.750 -0.0151 0.01367 0.00672 -0.0335 0.8545 0.8699
-1.500 0.0188 0.01375 0.00667 -0.0339 0.8471 0.8947
-1.250 0.0544 0.01381 0.00659 -0.0348 0.8398 0.9161
-1.000 0.0946 0.01384 0.00648 -0.0368 0.8326 0.9327
-0.750 0.1348 0.01384 0.00635 -0.0391 0.8249 0.9463
-0.500 0.1750 0.01379 0.00617 -0.0415 0.8174 0.9574
-0.250 0.2161 0.01373 0.00601 -0.0442 0.8086 0.9665
0.000 0.2554 0.01362 0.00581 -0.0466 0.8009 0.9749
0.250 0.2923 0.01357 0.00569 -0.0486 0.7909 0.9839
0.500 0.3305 0.01347 0.00553 -0.0510 0.7814 0.9917
0.750 0.3677 0.01336 0.00536 -0.0531 0.7723 0.9995
1.000 0.3890 0.01337 0.00534 -0.0520 0.7611 1.0000
1.250 0.4095 0.01340 0.00534 -0.0508 0.7499 1.0000
1.500 0.4302 0.01342 0.00533 -0.0495 0.7390 1.0000
1.750 0.4512 0.01345 0.00532 -0.0482 0.7284 1.0000
2.000 0.4723 0.01349 0.00536 -0.0470 0.7172 1.0000
2.250 0.4933 0.01356 0.00542 -0.0457 0.7052 1.0000
2.500 0.5146 0.01364 0.00550 -0.0445 0.6930 1.0000
2.750 0.5361 0.01372 0.00558 -0.0432 0.6805 1.0000
3.000 0.5579 0.01380 0.00569 -0.0420 0.6676 1.0000
3.250 0.5797 0.01389 0.00579 -0.0408 0.6540 1.0000
3.500 0.6018 0.01400 0.00590 -0.0396 0.6395 1.0000
3.750 0.6238 0.01411 0.00603 -0.0384 0.6241 1.0000
4.000 0.6458 0.01423 0.00620 -0.0372 0.6077 1.0000
4.250 0.6681 0.01436 0.00634 -0.0360 0.5905 1.0000
4.500 0.6901 0.01452 0.00654 -0.0348 0.5710 1.0000
4.750 0.7121 0.01469 0.00673 -0.0336 0.5499 1.0000
5.000 0.7340 0.01488 0.00699 -0.0324 0.5265 1.0000
5.250 0.7557 0.01511 0.00722 -0.0312 0.5004 1.0000
5.500 0.7770 0.01539 0.00748 -0.0299 0.4711 1.0000
5.750 0.7976 0.01573 0.00778 -0.0286 0.4385 1.0000
6.000 0.8176 0.01616 0.00813 -0.0272 0.4034 1.0000
6.250 0.8368 0.01669 0.00860 -0.0258 0.3664 1.0000
6.500 0.8553 0.01729 0.00911 -0.0244 0.3290 1.0000
6.750 0.8731 0.01799 0.00970 -0.0229 0.2927 1.0000
7.000 0.8905 0.01873 0.01035 -0.0215 0.2564 1.0000
7.250 0.9063 0.01960 0.01106 -0.0200 0.2161 1.0000
7.500 0.9206 0.02060 0.01183 -0.0184 0.1720 1.0000
7.750 0.9352 0.02163 0.01267 -0.0169 0.1332 1.0000
8.000 0.9502 0.02267 0.01364 -0.0155 0.1044 1.0000
8.250 0.9631 0.02389 0.01472 -0.0138 0.0759 1.0000
8.500 0.9748 0.02522 0.01596 -0.0119 0.0556 1.0000
8.750 0.9855 0.02659 0.01737 -0.0099 0.0459 1.0000
9.000 0.9935 0.02809 0.01887 -0.0077 0.0409 1.0000
9.250 1.0021 0.02941 0.02037 -0.0053 0.0374 1.0000
9.500 1.0092 0.03081 0.02189 -0.0030 0.0347 1.0000
9.750 1.0146 0.03238 0.02352 -0.0008 0.0323 1.0000
10.000 1.0210 0.03408 0.02532 0.0011 0.0304 1.0000
10.250 1.0303 0.03565 0.02713 0.0028 0.0283 1.0000
10.500 1.0390 0.03748 0.02911 0.0043 0.0270 1.0000
10.750 1.0480 0.03938 0.03117 0.0057 0.0259 1.0000
11.000 1.0565 0.04145 0.03339 0.0070 0.0249 1.0000
11.250 1.0628 0.04363 0.03567 0.0081 0.0238 1.0000
11.500 1.0681 0.04644 0.03858 0.0091 0.0226 1.0000
11.750 1.0705 0.04886 0.04133 0.0102 0.0216 1.0000
12.000 1.0711 0.05171 0.04448 0.0110 0.0208 1.0000
12.250 1.0689 0.05500 0.04805 0.0116 0.0203 1.0000
12.500 1.0633 0.05868 0.05202 0.0119 0.0199 1.0000
12.750 1.0546 0.06274 0.05634 0.0116 0.0196 1.0000
13.000 1.0432 0.06723 0.06109 0.0107 0.0194 1.0000
13.250 1.0297 0.07221 0.06632 0.0092 0.0194 1.0000
13.500 1.0131 0.07791 0.07226 0.0068 0.0192 1.0000
13.750 0.9946 0.08436 0.07893 0.0035 0.0192 1.0000
14.000 0.9740 0.09172 0.08650 -0.0008 0.0194 1.0000
14.250 0.9515 0.10026 0.09523 -0.0062 0.0197 1.0000
14.500 0.9264 0.11042 0.10555 -0.0128 0.0201 1.0000
14.750 0.8995 0.12232 0.11756 -0.0205 0.0206 1.0000
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Polar data table (+)
Polar graphs
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