SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 200,000 Max Cl/Cd: 65.55 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6060-il-200000-n5.txt Download as CSV file: xf-sd6060-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4939 0.08559 0.08218 -0.0260 1.0000 0.0114
-9.250 -0.4994 0.08003 0.07667 -0.0294 1.0000 0.0111
-9.000 -0.5077 0.07369 0.07039 -0.0340 1.0000 0.0109
-8.750 -0.5245 0.06542 0.06214 -0.0418 1.0000 0.0106
-8.500 -0.5441 0.05947 0.05612 -0.0441 1.0000 0.0104
-8.250 -0.5596 0.05320 0.04968 -0.0450 1.0000 0.0101
-8.000 -0.5745 0.04665 0.04285 -0.0441 1.0000 0.0098
-7.750 -0.5890 0.04093 0.03673 -0.0411 1.0000 0.0095
-7.500 -0.5811 0.03510 0.03031 -0.0413 0.9894 0.0093
-7.250 -0.5599 0.03076 0.02538 -0.0426 0.9796 0.0094
-7.000 -0.5349 0.02748 0.02159 -0.0436 0.9714 0.0095
-6.750 -0.5094 0.02510 0.01880 -0.0440 0.9624 0.0099
-6.500 -0.4810 0.02304 0.01638 -0.0447 0.9554 0.0103
-6.250 -0.4538 0.02166 0.01474 -0.0450 0.9467 0.0112
-6.000 -0.4262 0.02039 0.01318 -0.0451 0.9386 0.0123
-5.750 -0.3994 0.01908 0.01164 -0.0449 0.9305 0.0130
-5.500 -0.3746 0.01793 0.01032 -0.0443 0.9212 0.0134
-5.250 -0.3510 0.01671 0.00899 -0.0436 0.9127 0.0141
-5.000 -0.3275 0.01588 0.00808 -0.0429 0.9035 0.0151
-4.750 -0.3036 0.01522 0.00732 -0.0421 0.8943 0.0166
-4.500 -0.2791 0.01467 0.00660 -0.0413 0.8864 0.0190
-4.250 -0.2552 0.01408 0.00599 -0.0406 0.8769 0.0251
-4.000 -0.2314 0.01344 0.00533 -0.0397 0.8685 0.0384
-3.750 -0.2072 0.01293 0.00489 -0.0391 0.8601 0.0648
-3.500 -0.1839 0.01232 0.00456 -0.0385 0.8512 0.1232
-3.250 -0.1604 0.01175 0.00421 -0.0378 0.8436 0.1920
-3.000 -0.1371 0.01118 0.00393 -0.0372 0.8344 0.2763
-2.750 -0.1148 0.01056 0.00368 -0.0364 0.8262 0.3859
-2.500 -0.0934 0.00995 0.00351 -0.0352 0.8178 0.5093
-2.250 -0.0716 0.00952 0.00345 -0.0338 0.8093 0.6179
-2.000 -0.0483 0.00930 0.00340 -0.0324 0.8018 0.6962
-1.750 -0.0238 0.00920 0.00339 -0.0313 0.7929 0.7482
-1.500 0.0014 0.00916 0.00335 -0.0303 0.7852 0.7866
-1.250 0.0268 0.00915 0.00334 -0.0293 0.7766 0.8174
-1.000 0.0524 0.00916 0.00331 -0.0284 0.7684 0.8441
-0.750 0.0786 0.00919 0.00329 -0.0276 0.7604 0.8665
-0.500 0.1052 0.00923 0.00329 -0.0269 0.7516 0.8868
-0.250 0.1336 0.00928 0.00326 -0.0266 0.7438 0.9041
0.000 0.1633 0.00932 0.00325 -0.0267 0.7345 0.9188
0.250 0.1939 0.00936 0.00323 -0.0271 0.7257 0.9311
0.500 0.2246 0.00940 0.00318 -0.0275 0.7169 0.9423
0.750 0.2597 0.00943 0.00317 -0.0290 0.7067 0.9495
1.000 0.2921 0.00947 0.00315 -0.0299 0.6968 0.9577
1.250 0.3276 0.00950 0.00312 -0.0315 0.6869 0.9637
1.500 0.3606 0.00954 0.00312 -0.0326 0.6760 0.9708
1.750 0.3975 0.00957 0.00311 -0.0346 0.6647 0.9755
2.000 0.4317 0.00961 0.00312 -0.0361 0.6531 0.9815
2.250 0.4673 0.00965 0.00314 -0.0378 0.6407 0.9863
2.500 0.5020 0.00970 0.00316 -0.0394 0.6275 0.9917
2.750 0.5365 0.00975 0.00319 -0.0410 0.6132 0.9971
3.000 0.5656 0.00982 0.00326 -0.0415 0.5983 1.0000
3.250 0.5875 0.00992 0.00334 -0.0404 0.5834 1.0000
3.500 0.6095 0.01003 0.00343 -0.0394 0.5671 1.0000
3.750 0.6314 0.01016 0.00356 -0.0383 0.5494 1.0000
4.000 0.6532 0.01031 0.00368 -0.0372 0.5296 1.0000
4.250 0.6751 0.01049 0.00382 -0.0361 0.5075 1.0000
4.500 0.6967 0.01070 0.00399 -0.0350 0.4831 1.0000
4.750 0.7179 0.01096 0.00418 -0.0339 0.4549 1.0000
5.000 0.7387 0.01127 0.00442 -0.0327 0.4244 1.0000
5.250 0.7591 0.01165 0.00469 -0.0314 0.3918 1.0000
5.500 0.7794 0.01207 0.00500 -0.0302 0.3564 1.0000
5.750 0.7993 0.01256 0.00536 -0.0290 0.3212 1.0000
6.000 0.8192 0.01309 0.00577 -0.0279 0.2846 1.0000
6.250 0.8381 0.01372 0.00625 -0.0267 0.2434 1.0000
6.500 0.8569 0.01439 0.00674 -0.0255 0.2034 1.0000
6.750 0.8755 0.01511 0.00728 -0.0244 0.1660 1.0000
7.000 0.8937 0.01586 0.00785 -0.0232 0.1300 1.0000
7.250 0.9125 0.01659 0.00846 -0.0221 0.1025 1.0000
7.500 0.9314 0.01729 0.00910 -0.0210 0.0793 1.0000
7.750 0.9490 0.01811 0.00982 -0.0198 0.0568 1.0000
8.000 0.9655 0.01904 0.01071 -0.0183 0.0395 1.0000
8.250 0.9814 0.01999 0.01165 -0.0168 0.0306 1.0000
8.500 0.9982 0.02082 0.01257 -0.0154 0.0261 1.0000
8.750 1.0120 0.02187 0.01366 -0.0137 0.0229 1.0000
9.000 1.0269 0.02275 0.01467 -0.0121 0.0216 1.0000
9.250 1.0399 0.02372 0.01578 -0.0102 0.0204 1.0000
9.500 1.0499 0.02474 0.01692 -0.0080 0.0194 1.0000
9.750 1.0586 0.02585 0.01817 -0.0057 0.0186 1.0000
10.000 1.0672 0.02702 0.01943 -0.0037 0.0176 1.0000
10.250 1.0720 0.02856 0.02104 -0.0015 0.0165 1.0000
10.500 1.0768 0.03025 0.02283 0.0005 0.0155 1.0000
10.750 1.0851 0.03172 0.02445 0.0021 0.0151 1.0000
11.000 1.0927 0.03338 0.02627 0.0036 0.0145 1.0000
11.250 1.1000 0.03511 0.02815 0.0050 0.0139 1.0000
11.500 1.1067 0.03688 0.03007 0.0062 0.0132 1.0000
11.750 1.1123 0.03856 0.03186 0.0070 0.0122 1.0000
12.000 1.1159 0.04063 0.03405 0.0079 0.0117 1.0000
12.250 1.1171 0.04307 0.03660 0.0086 0.0111 1.0000
12.500 1.1149 0.04630 0.04003 0.0095 0.0107 1.0000
12.750 1.1136 0.04935 0.04328 0.0099 0.0104 1.0000
13.000 1.1118 0.05240 0.04657 0.0100 0.0101 1.0000
13.250 1.1080 0.05585 0.05024 0.0098 0.0100 1.0000
13.500 1.1007 0.05988 0.05452 0.0091 0.0097 1.0000
13.750 1.0918 0.06428 0.05915 0.0080 0.0095 1.0000
14.000 1.0811 0.06911 0.06421 0.0063 0.0094 1.0000
14.250 1.0689 0.07446 0.06976 0.0040 0.0095 1.0000
14.500 1.0549 0.08045 0.07597 0.0011 0.0093 1.0000
14.750 1.0397 0.08714 0.08286 -0.0027 0.0091 1.0000
15.000 1.0226 0.09464 0.09055 -0.0069 0.0093 1.0000
15.250 1.0062 0.10256 0.09865 -0.0118 0.0093 1.0000
15.500 0.9867 0.11174 0.10800 -0.0174 0.0094 1.0000
15.750 0.9647 0.12214 0.11855 -0.0238 0.0096 1.0000
16.000 0.9444 0.13269 0.12922 -0.0302 0.0099 1.0000
16.250 0.9196 0.14543 0.14203 -0.0376 0.0101 1.0000
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Polar data table (+)
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