SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD5060 (9.5%) (sd5060-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.86 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd5060-il-1000000-n5.txt Download as CSV file: xf-sd5060-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD5060 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.8407 0.09568 0.09369 -0.0110 1.0000 0.0056
-14.250 -0.9158 0.07786 0.07573 -0.0223 1.0000 0.0054
-14.000 -0.9889 0.06162 0.05934 -0.0330 1.0000 0.0052
-13.750 -1.0742 0.04044 0.03782 -0.0505 1.0000 0.0050
-13.500 -1.1111 0.03338 0.03051 -0.0555 1.0000 0.0050
-13.250 -1.1067 0.03121 0.02821 -0.0556 1.0000 0.0051
-13.000 -1.0981 0.02926 0.02611 -0.0554 1.0000 0.0052
-12.750 -1.0852 0.02762 0.02433 -0.0552 1.0000 0.0053
-12.500 -1.0701 0.02612 0.02269 -0.0550 1.0000 0.0054
-12.250 -1.0528 0.02480 0.02124 -0.0547 1.0000 0.0056
-12.000 -1.0343 0.02353 0.01985 -0.0545 1.0000 0.0057
-11.750 -1.0137 0.02252 0.01872 -0.0542 1.0000 0.0058
-11.500 -0.9928 0.02149 0.01755 -0.0540 1.0000 0.0059
-11.250 -0.9713 0.02046 0.01641 -0.0538 1.0000 0.0060
-11.000 -0.9498 0.01938 0.01521 -0.0535 1.0000 0.0063
-10.750 -0.9259 0.01872 0.01451 -0.0534 1.0000 0.0066
-10.500 -0.9013 0.01818 0.01391 -0.0532 1.0000 0.0068
-10.250 -0.8762 0.01770 0.01340 -0.0530 1.0000 0.0070
-10.000 -0.8513 0.01715 0.01279 -0.0529 1.0000 0.0073
-9.750 -0.8223 0.01662 0.01218 -0.0535 0.9874 0.0076
-9.500 -0.7910 0.01607 0.01156 -0.0546 0.9740 0.0080
-9.250 -0.7627 0.01554 0.01094 -0.0551 0.9602 0.0083
-9.000 -0.7376 0.01504 0.01033 -0.0547 0.9462 0.0085
-8.750 -0.7132 0.01460 0.00979 -0.0541 0.9337 0.0087
-8.500 -0.6885 0.01421 0.00931 -0.0536 0.9225 0.0088
-8.250 -0.6652 0.01340 0.00835 -0.0530 0.9116 0.0092
-8.000 -0.6398 0.01293 0.00781 -0.0526 0.9014 0.0096
-7.750 -0.6137 0.01259 0.00742 -0.0523 0.8920 0.0100
-7.500 -0.5875 0.01229 0.00705 -0.0520 0.8829 0.0104
-7.250 -0.5609 0.01195 0.00663 -0.0518 0.8736 0.0108
-7.000 -0.5342 0.01159 0.00619 -0.0515 0.8649 0.0112
-6.750 -0.5075 0.01126 0.00577 -0.0513 0.8559 0.0116
-6.500 -0.4803 0.01094 0.00539 -0.0511 0.8473 0.0119
-6.250 -0.4531 0.01070 0.00507 -0.0509 0.8387 0.0122
-6.000 -0.4256 0.01045 0.00476 -0.0508 0.8299 0.0125
-5.750 -0.3987 0.00998 0.00418 -0.0506 0.8216 0.0131
-5.500 -0.3712 0.00965 0.00379 -0.0505 0.8126 0.0136
-5.250 -0.3435 0.00938 0.00347 -0.0504 0.8042 0.0142
-4.750 -0.2879 0.00895 0.00292 -0.0502 0.7866 0.0154
-4.500 -0.2599 0.00877 0.00268 -0.0501 0.7780 0.0161
-4.250 -0.2318 0.00861 0.00247 -0.0500 0.7687 0.0168
-4.000 -0.2037 0.00844 0.00225 -0.0499 0.7598 0.0178
-3.750 -0.1757 0.00828 0.00205 -0.0498 0.7506 0.0198
-3.500 -0.1474 0.00812 0.00187 -0.0498 0.7411 0.0234
-3.250 -0.1196 0.00783 0.00166 -0.0498 0.7317 0.0467
-3.000 -0.0917 0.00764 0.00151 -0.0497 0.7218 0.0653
-2.750 -0.0635 0.00746 0.00137 -0.0497 0.7115 0.0873
-2.500 -0.0354 0.00729 0.00127 -0.0497 0.7012 0.1107
-2.250 -0.0072 0.00718 0.00117 -0.0497 0.6903 0.1302
-2.000 0.0209 0.00707 0.00109 -0.0497 0.6786 0.1506
-1.750 0.0492 0.00698 0.00103 -0.0497 0.6661 0.1706
-1.500 0.0775 0.00692 0.00097 -0.0497 0.6533 0.1866
-1.250 0.1057 0.00684 0.00092 -0.0496 0.6394 0.2090
-1.000 0.1338 0.00674 0.00088 -0.0497 0.6242 0.2434
-0.750 0.1618 0.00667 0.00085 -0.0496 0.6076 0.2757
-0.500 0.1899 0.00665 0.00083 -0.0496 0.5903 0.2980
-0.250 0.2181 0.00662 0.00082 -0.0496 0.5728 0.3253
0.000 0.2462 0.00660 0.00082 -0.0496 0.5551 0.3516
0.250 0.2742 0.00658 0.00083 -0.0496 0.5366 0.3840
0.500 0.3021 0.00658 0.00085 -0.0496 0.5170 0.4170
0.750 0.3300 0.00658 0.00087 -0.0496 0.4958 0.4545
1.000 0.3577 0.00660 0.00092 -0.0495 0.4726 0.4940
1.250 0.3854 0.00663 0.00097 -0.0495 0.4475 0.5366
1.500 0.4129 0.00665 0.00104 -0.0494 0.4246 0.5821
1.750 0.4402 0.00669 0.00112 -0.0493 0.3997 0.6315
2.000 0.4673 0.00673 0.00121 -0.0492 0.3738 0.6825
2.250 0.4940 0.00678 0.00132 -0.0490 0.3475 0.7378
2.500 0.5199 0.00681 0.00144 -0.0485 0.3210 0.8015
2.750 0.5439 0.00680 0.00157 -0.0476 0.3001 0.8744
3.000 0.5704 0.00680 0.00167 -0.0470 0.2796 0.9640
3.250 0.6037 0.00704 0.00179 -0.0483 0.2536 1.0000
3.500 0.6310 0.00726 0.00193 -0.0481 0.2333 1.0000
3.750 0.6582 0.00747 0.00206 -0.0480 0.2173 1.0000
4.000 0.6854 0.00770 0.00221 -0.0479 0.2008 1.0000
4.250 0.7125 0.00794 0.00237 -0.0478 0.1844 1.0000
4.500 0.7396 0.00816 0.00253 -0.0477 0.1717 1.0000
4.750 0.7667 0.00837 0.00269 -0.0476 0.1599 1.0000
5.000 0.7937 0.00860 0.00287 -0.0474 0.1476 1.0000
5.250 0.8207 0.00883 0.00306 -0.0473 0.1378 1.0000
5.500 0.8475 0.00908 0.00326 -0.0471 0.1272 1.0000
5.750 0.8743 0.00932 0.00346 -0.0470 0.1188 1.0000
6.000 0.9010 0.00955 0.00367 -0.0468 0.1112 1.0000
6.250 0.9274 0.00983 0.00392 -0.0466 0.1015 1.0000
6.500 0.9540 0.01007 0.00415 -0.0464 0.0953 1.0000
6.750 0.9803 0.01035 0.00439 -0.0462 0.0885 1.0000
7.000 1.0065 0.01061 0.00465 -0.0460 0.0823 1.0000
7.250 1.0324 0.01092 0.00493 -0.0457 0.0748 1.0000
7.500 1.0578 0.01128 0.00525 -0.0455 0.0657 1.0000
7.750 1.0836 0.01158 0.00554 -0.0452 0.0599 1.0000
8.000 1.1086 0.01197 0.00589 -0.0448 0.0524 1.0000
8.250 1.1330 0.01241 0.00628 -0.0444 0.0437 1.0000
8.500 1.1574 0.01285 0.00669 -0.0440 0.0365 1.0000
8.750 1.1817 0.01328 0.00711 -0.0436 0.0311 1.0000
9.000 1.2054 0.01376 0.00756 -0.0431 0.0259 1.0000
9.250 1.2294 0.01419 0.00800 -0.0426 0.0228 1.0000
9.500 1.2525 0.01469 0.00849 -0.0421 0.0192 1.0000
9.750 1.2758 0.01515 0.00898 -0.0416 0.0166 1.0000
10.000 1.2981 0.01571 0.00953 -0.0409 0.0136 1.0000
10.250 1.3197 0.01631 0.01013 -0.0402 0.0106 1.0000
10.500 1.3408 0.01693 0.01077 -0.0394 0.0080 1.0000
10.750 1.3612 0.01760 0.01145 -0.0385 0.0059 1.0000
11.000 1.3814 0.01824 0.01213 -0.0376 0.0050 1.0000
11.250 1.4011 0.01889 0.01283 -0.0367 0.0044 1.0000
11.500 1.4200 0.01956 0.01356 -0.0356 0.0040 1.0000
11.750 1.4375 0.02032 0.01438 -0.0344 0.0036 1.0000
12.000 1.4545 0.02105 0.01517 -0.0332 0.0033 1.0000
12.250 1.4705 0.02177 0.01597 -0.0318 0.0033 1.0000
12.500 1.4839 0.02253 0.01680 -0.0300 0.0032 1.0000
12.750 1.4936 0.02332 0.01766 -0.0277 0.0030 1.0000
13.000 1.5018 0.02422 0.01864 -0.0254 0.0029 1.0000
13.250 1.5092 0.02523 0.01974 -0.0233 0.0028 1.0000
13.500 1.5165 0.02634 0.02094 -0.0214 0.0028 1.0000
13.750 1.5221 0.02765 0.02233 -0.0196 0.0027 1.0000
14.000 1.5267 0.02912 0.02389 -0.0181 0.0026 1.0000
14.250 1.5307 0.03074 0.02561 -0.0167 0.0025 1.0000
14.500 1.5331 0.03261 0.02757 -0.0156 0.0025 1.0000
14.750 1.5343 0.03471 0.02977 -0.0147 0.0024 1.0000
15.000 1.5336 0.03715 0.03233 -0.0140 0.0024 1.0000
15.250 1.5311 0.03992 0.03521 -0.0138 0.0023 1.0000
15.500 1.5262 0.04316 0.03857 -0.0139 0.0023 1.0000
15.750 1.5212 0.04663 0.04216 -0.0144 0.0022 1.0000
16.000 1.5110 0.05098 0.04666 -0.0156 0.0022 1.0000
16.250 1.5004 0.05570 0.05151 -0.0172 0.0022 1.0000
16.500 1.4867 0.06117 0.05713 -0.0194 0.0021 1.0000
16.750 1.4682 0.06785 0.06397 -0.0226 0.0021 1.0000
17.000 1.4499 0.07491 0.07119 -0.0263 0.0021 1.0000
17.250 1.4305 0.08258 0.07901 -0.0304 0.0021 1.0000
17.500 1.4065 0.09148 0.08807 -0.0353 0.0021 1.0000
17.750 1.3802 0.10121 0.09797 -0.0408 0.0021 1.0000
18.000 1.3545 0.11107 0.10798 -0.0464 0.0022 1.0000
18.250 1.3222 0.12263 0.11971 -0.0531 0.0022 1.0000
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Polar data table (+)
Polar graphs
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