SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 200,000 Max Cl/Cd: 70.37 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6060-il-200000.txt Download as CSV file: xf-sd6060-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3807 0.08823 0.08507 -0.0249 1.0000 0.0488
-9.250 -0.3829 0.08372 0.08058 -0.0267 1.0000 0.0505
-9.000 -0.3889 0.07866 0.07555 -0.0294 1.0000 0.0524
-8.750 -0.3982 0.07317 0.07013 -0.0330 1.0000 0.0535
-8.500 -0.4161 0.06642 0.06342 -0.0396 1.0000 0.0543
-8.250 -0.4354 0.06064 0.05763 -0.0443 1.0000 0.0543
-8.000 -0.4595 0.05655 0.05346 -0.0455 1.0000 0.0546
-7.750 -0.4810 0.05336 0.05010 -0.0449 1.0000 0.0551
-7.500 -0.4995 0.05139 0.04803 -0.0411 1.0000 0.0553
-7.250 -0.5186 0.04993 0.04647 -0.0364 1.0000 0.0554
-7.000 -0.5521 0.05788 0.05383 -0.0350 1.0000 0.0554
-6.000 -0.4970 0.03284 0.02734 -0.0353 0.9857 0.0313
-5.750 -0.4675 0.02865 0.02266 -0.0368 0.9802 0.0307
-5.500 -0.4343 0.02575 0.01925 -0.0381 0.9745 0.0310
-5.250 -0.3974 0.02248 0.01552 -0.0400 0.9712 0.0300
-5.000 -0.3639 0.02036 0.01308 -0.0409 0.9653 0.0299
-4.750 -0.3258 0.01860 0.01111 -0.0427 0.9610 0.0309
-4.500 -0.2872 0.01678 0.00919 -0.0447 0.9577 0.0335
-4.250 -0.2563 0.01585 0.00826 -0.0455 0.9501 0.0406
-4.000 -0.2223 0.01465 0.00703 -0.0467 0.9446 0.0547
-3.750 -0.1978 0.01332 0.00609 -0.0463 0.9356 0.1238
-3.500 -0.1715 0.01204 0.00561 -0.0468 0.9291 0.2852
-3.250 -0.1557 0.01096 0.00539 -0.0448 0.9184 0.4906
-3.000 -0.1370 0.01037 0.00541 -0.0424 0.9096 0.6535
-2.750 -0.1138 0.01020 0.00545 -0.0404 0.9021 0.7436
-2.500 -0.0918 0.01021 0.00551 -0.0384 0.8929 0.7965
-2.250 -0.0672 0.01025 0.00552 -0.0366 0.8865 0.8340
-2.000 -0.0447 0.01036 0.00558 -0.0345 0.8768 0.8640
-1.750 -0.0199 0.01047 0.00560 -0.0329 0.8696 0.8888
-1.500 0.0072 0.01058 0.00563 -0.0318 0.8613 0.9093
-1.250 0.0371 0.01069 0.00563 -0.0314 0.8539 0.9280
-1.000 0.0762 0.01078 0.00561 -0.0329 0.8467 0.9424
-0.750 0.1271 0.01084 0.00554 -0.0370 0.8406 0.9520
-0.500 0.1770 0.01083 0.00543 -0.0412 0.8330 0.9617
-0.250 0.2207 0.01079 0.00530 -0.0443 0.8252 0.9717
0.000 0.2660 0.01070 0.00511 -0.0479 0.8168 0.9801
0.250 0.3093 0.01058 0.00493 -0.0512 0.8071 0.9879
0.500 0.3509 0.01043 0.00470 -0.0542 0.7983 0.9955
0.750 0.3855 0.01028 0.00451 -0.0559 0.7880 1.0000
1.000 0.4059 0.01024 0.00444 -0.0547 0.7769 1.0000
1.250 0.4267 0.01021 0.00436 -0.0536 0.7665 1.0000
1.500 0.4477 0.01016 0.00425 -0.0523 0.7566 1.0000
1.750 0.4689 0.01015 0.00423 -0.0512 0.7453 1.0000
2.000 0.4902 0.01015 0.00421 -0.0501 0.7338 1.0000
2.250 0.5115 0.01016 0.00420 -0.0489 0.7226 1.0000
2.500 0.5330 0.01017 0.00419 -0.0477 0.7112 1.0000
2.750 0.5547 0.01020 0.00417 -0.0464 0.6998 1.0000
3.000 0.5764 0.01024 0.00422 -0.0452 0.6871 1.0000
3.250 0.5981 0.01029 0.00427 -0.0440 0.6737 1.0000
3.500 0.6200 0.01035 0.00433 -0.0428 0.6600 1.0000
3.750 0.6420 0.01041 0.00439 -0.0416 0.6455 1.0000
4.000 0.6641 0.01050 0.00448 -0.0404 0.6304 1.0000
4.250 0.6863 0.01059 0.00458 -0.0393 0.6140 1.0000
4.500 0.7084 0.01069 0.00471 -0.0381 0.5953 1.0000
4.750 0.7306 0.01081 0.00482 -0.0369 0.5756 1.0000
5.000 0.7526 0.01094 0.00498 -0.0357 0.5534 1.0000
5.250 0.7744 0.01111 0.00512 -0.0345 0.5280 1.0000
5.500 0.7960 0.01132 0.00530 -0.0333 0.4982 1.0000
5.750 0.8170 0.01161 0.00552 -0.0320 0.4635 1.0000
6.000 0.8370 0.01200 0.00581 -0.0306 0.4228 1.0000
6.250 0.8559 0.01252 0.00615 -0.0291 0.3772 1.0000
6.500 0.8738 0.01317 0.00658 -0.0277 0.3273 1.0000
6.750 0.8912 0.01389 0.00709 -0.0262 0.2781 1.0000
7.000 0.9089 0.01464 0.00765 -0.0249 0.2345 1.0000
7.250 0.9268 0.01540 0.00827 -0.0236 0.1946 1.0000
7.500 0.9442 0.01623 0.00894 -0.0223 0.1555 1.0000
7.750 0.9590 0.01730 0.00977 -0.0207 0.1098 1.0000
8.000 0.9655 0.01921 0.01125 -0.0179 0.0586 1.0000
8.250 0.9765 0.02061 0.01264 -0.0156 0.0461 1.0000
8.500 0.9907 0.02168 0.01376 -0.0138 0.0403 1.0000
8.750 0.9975 0.02343 0.01551 -0.0111 0.0369 1.0000
9.000 1.0120 0.02461 0.01682 -0.0093 0.0352 1.0000
9.250 1.0259 0.02587 0.01820 -0.0074 0.0329 1.0000
9.500 1.0391 0.02712 0.01951 -0.0057 0.0307 1.0000
9.750 1.0529 0.02905 0.02145 -0.0042 0.0285 1.0000
10.000 1.0763 0.03201 0.02458 -0.0041 0.0272 1.0000
10.250 1.0933 0.03392 0.02673 -0.0028 0.0265 1.0000
10.500 1.1065 0.03584 0.02891 -0.0012 0.0254 1.0000
10.750 1.1155 0.03765 0.03094 0.0008 0.0242 1.0000
11.000 1.1223 0.03959 0.03309 0.0028 0.0231 1.0000
11.250 1.1267 0.04223 0.03599 0.0049 0.0227 1.0000
11.500 1.1267 0.04504 0.03910 0.0070 0.0224 1.0000
11.750 1.1209 0.04825 0.04262 0.0092 0.0224 1.0000
12.000 1.1088 0.05193 0.04663 0.0112 0.0226 1.0000
12.250 1.0939 0.05583 0.05082 0.0124 0.0227 1.0000
12.500 1.0746 0.06037 0.05566 0.0129 0.0231 1.0000
12.750 1.0526 0.06558 0.06114 0.0123 0.0235 1.0000
13.000 1.0312 0.07108 0.06687 0.0107 0.0237 1.0000
13.250 1.0086 0.07728 0.07329 0.0081 0.0241 1.0000
13.500 0.9843 0.08434 0.08051 0.0042 0.0244 1.0000
13.750 0.9599 0.09225 0.08858 -0.0008 0.0246 1.0000
14.000 0.9340 0.10150 0.09797 -0.0070 0.0250 1.0000
14.250 0.9064 0.11261 0.10919 -0.0146 0.0256 1.0000
14.500 0.8785 0.12525 0.12188 -0.0224 0.0264 1.0000
14.750 0.8594 0.13587 0.13249 -0.0278 0.0273 1.0000
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Polar data table (+)
Polar graphs
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