SD6060-104-88 (sd6060-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6060-104-88 (sd6060-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.96 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6060-il-1000000-n5.txt Download as CSV file: xf-sd6060-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7142 0.04098 0.03906 -0.0457 1.0000 0.0029
-9.500 -0.7267 0.03284 0.03034 -0.0472 0.9633 0.0029
-9.250 -0.7178 0.03012 0.02731 -0.0463 0.9417 0.0029
-9.000 -0.7091 0.02788 0.02478 -0.0445 0.9248 0.0030
-8.750 -0.7028 0.02489 0.02139 -0.0424 0.9104 0.0030
-8.500 -0.6920 0.02229 0.01839 -0.0406 0.8987 0.0030
-8.250 -0.6765 0.02026 0.01604 -0.0392 0.8882 0.0030
-8.000 -0.6599 0.01818 0.01362 -0.0379 0.8786 0.0030
-7.750 -0.6410 0.01648 0.01163 -0.0367 0.8697 0.0031
-7.500 -0.6192 0.01534 0.01029 -0.0359 0.8609 0.0032
-7.250 -0.5964 0.01438 0.00916 -0.0352 0.8527 0.0033
-6.750 -0.5479 0.01304 0.00758 -0.0342 0.8362 0.0035
-6.500 -0.5229 0.01252 0.00695 -0.0338 0.8282 0.0037
-6.250 -0.4975 0.01202 0.00638 -0.0334 0.8198 0.0038
-6.000 -0.4719 0.01157 0.00583 -0.0331 0.8120 0.0040
-5.750 -0.4461 0.01114 0.00531 -0.0328 0.8036 0.0043
-5.500 -0.4199 0.01078 0.00486 -0.0325 0.7955 0.0046
-5.000 -0.3671 0.01011 0.00404 -0.0321 0.7791 0.0050
-4.750 -0.3404 0.00984 0.00369 -0.0319 0.7711 0.0052
-4.500 -0.3137 0.00950 0.00328 -0.0317 0.7626 0.0054
-4.250 -0.2871 0.00919 0.00289 -0.0315 0.7546 0.0065
-4.000 -0.2600 0.00898 0.00263 -0.0314 0.7461 0.0072
-3.750 -0.2326 0.00879 0.00238 -0.0313 0.7378 0.0081
-3.500 -0.2053 0.00861 0.00216 -0.0312 0.7296 0.0105
-3.250 -0.1781 0.00838 0.00195 -0.0311 0.7210 0.0198
-3.000 -0.1509 0.00817 0.00177 -0.0310 0.7128 0.0353
-2.750 -0.1239 0.00794 0.00161 -0.0310 0.7042 0.0600
-2.500 -0.0968 0.00771 0.00148 -0.0309 0.6957 0.0917
-2.250 -0.0696 0.00753 0.00136 -0.0309 0.6872 0.1205
-2.000 -0.0428 0.00724 0.00123 -0.0309 0.6785 0.1766
-1.750 -0.0165 0.00690 0.00112 -0.0308 0.6700 0.2534
-1.500 0.0101 0.00663 0.00103 -0.0307 0.6611 0.3217
-1.250 0.0369 0.00637 0.00094 -0.0307 0.6521 0.3888
-1.000 0.0633 0.00610 0.00088 -0.0306 0.6430 0.4666
-0.750 0.0898 0.00585 0.00083 -0.0305 0.6334 0.5426
-0.500 0.1164 0.00564 0.00080 -0.0303 0.6243 0.6090
-0.250 0.1434 0.00552 0.00079 -0.0302 0.6154 0.6588
0.000 0.1705 0.00543 0.00080 -0.0300 0.6060 0.7010
0.250 0.1977 0.00537 0.00081 -0.0299 0.5965 0.7362
0.500 0.2250 0.00535 0.00083 -0.0298 0.5867 0.7632
0.750 0.2525 0.00535 0.00085 -0.0297 0.5760 0.7861
1.000 0.2797 0.00535 0.00089 -0.0295 0.5647 0.8087
1.250 0.3070 0.00537 0.00093 -0.0294 0.5525 0.8286
1.500 0.3341 0.00541 0.00097 -0.0292 0.5392 0.8455
1.750 0.3611 0.00547 0.00103 -0.0290 0.5238 0.8607
2.000 0.3880 0.00555 0.00108 -0.0288 0.5071 0.8742
2.250 0.4149 0.00565 0.00115 -0.0286 0.4891 0.8863
2.500 0.4414 0.00576 0.00123 -0.0284 0.4680 0.8974
2.750 0.4676 0.00591 0.00132 -0.0281 0.4450 0.9072
3.000 0.4937 0.00607 0.00141 -0.0278 0.4213 0.9168
3.250 0.5196 0.00625 0.00153 -0.0274 0.3961 0.9268
3.500 0.5451 0.00645 0.00165 -0.0270 0.3709 0.9361
3.750 0.5707 0.00667 0.00179 -0.0267 0.3440 0.9452
4.000 0.5966 0.00689 0.00194 -0.0264 0.3194 0.9544
4.250 0.6235 0.00717 0.00211 -0.0264 0.2880 0.9624
4.500 0.6497 0.00760 0.00233 -0.0264 0.2406 0.9708
4.750 0.6786 0.00808 0.00259 -0.0271 0.1935 0.9772
5.000 0.7075 0.00846 0.00284 -0.0277 0.1603 0.9836
5.250 0.7390 0.00881 0.00307 -0.0289 0.1363 0.9879
5.500 0.7694 0.00916 0.00333 -0.0298 0.1147 0.9928
5.750 0.8002 0.00950 0.00359 -0.0309 0.0953 0.9973
6.000 0.8266 0.00994 0.00391 -0.0310 0.0714 1.0000
6.250 0.8479 0.01036 0.00424 -0.0300 0.0523 1.0000
6.500 0.8700 0.01078 0.00458 -0.0292 0.0364 1.0000
6.750 0.8912 0.01132 0.00500 -0.0283 0.0188 1.0000
7.000 0.9145 0.01168 0.00535 -0.0276 0.0145 1.0000
7.250 0.9380 0.01202 0.00570 -0.0271 0.0130 1.0000
7.500 0.9614 0.01238 0.00608 -0.0265 0.0118 1.0000
7.750 0.9845 0.01277 0.00653 -0.0258 0.0109 1.0000
8.000 1.0075 0.01316 0.00697 -0.0252 0.0105 1.0000
8.250 1.0307 0.01351 0.00736 -0.0246 0.0102 1.0000
8.500 1.0537 0.01388 0.00776 -0.0240 0.0097 1.0000
8.750 1.0762 0.01427 0.00819 -0.0234 0.0092 1.0000
9.000 1.0982 0.01470 0.00866 -0.0227 0.0088 1.0000
9.250 1.1196 0.01516 0.00918 -0.0219 0.0083 1.0000
9.500 1.1401 0.01568 0.00973 -0.0210 0.0077 1.0000
9.750 1.1580 0.01639 0.01050 -0.0197 0.0069 1.0000
10.000 1.1783 0.01685 0.01101 -0.0188 0.0067 1.0000
10.250 1.1988 0.01726 0.01146 -0.0180 0.0064 1.0000
10.500 1.2175 0.01778 0.01204 -0.0169 0.0061 1.0000
10.750 1.2360 0.01827 0.01257 -0.0158 0.0057 1.0000
11.000 1.2521 0.01880 0.01316 -0.0142 0.0053 1.0000
11.250 1.2668 0.01930 0.01370 -0.0125 0.0049 1.0000
11.500 1.2793 0.01993 0.01438 -0.0105 0.0047 1.0000
11.750 1.2907 0.02067 0.01515 -0.0085 0.0042 1.0000
12.000 1.3015 0.02147 0.01603 -0.0066 0.0041 1.0000
12.250 1.3135 0.02222 0.01685 -0.0050 0.0039 1.0000
12.500 1.3251 0.02304 0.01773 -0.0034 0.0036 1.0000
12.750 1.3356 0.02397 0.01872 -0.0019 0.0033 1.0000
13.000 1.3459 0.02494 0.01975 -0.0005 0.0030 1.0000
13.250 1.3554 0.02601 0.02089 0.0008 0.0028 1.0000
13.500 1.3617 0.02739 0.02233 0.0022 0.0025 1.0000
13.750 1.3682 0.02881 0.02383 0.0035 0.0023 1.0000
14.000 1.3736 0.03038 0.02550 0.0046 0.0023 1.0000
14.250 1.3783 0.03208 0.02729 0.0055 0.0023 1.0000
14.500 1.3831 0.03384 0.02915 0.0063 0.0021 1.0000
14.750 1.3859 0.03589 0.03130 0.0068 0.0019 1.0000
15.000 1.3869 0.03820 0.03372 0.0073 0.0020 1.0000
15.250 1.3894 0.04045 0.03606 0.0075 0.0018 1.0000
15.500 1.3877 0.04327 0.03899 0.0075 0.0018 1.0000
15.750 1.3858 0.04622 0.04204 0.0072 0.0017 1.0000
16.000 1.3825 0.04949 0.04544 0.0067 0.0017 1.0000
16.250 1.3765 0.05326 0.04932 0.0058 0.0017 1.0000
16.500 1.3704 0.05725 0.05342 0.0045 0.0016 1.0000
16.750 1.3625 0.06172 0.05803 0.0029 0.0016 1.0000
17.000 1.3529 0.06667 0.06309 0.0009 0.0016 1.0000
17.250 1.3418 0.07209 0.06865 -0.0016 0.0016 1.0000
17.500 1.3245 0.07889 0.07559 -0.0049 0.0015 1.0000
17.750 1.3053 0.08634 0.08320 -0.0088 0.0014 1.0000
18.000 1.2924 0.09290 0.08988 -0.0123 0.0015 1.0000
18.250 1.2702 0.10152 0.09865 -0.0170 0.0015 1.0000
18.500 1.2502 0.10991 0.10719 -0.0217 0.0015 1.0000
18.750 1.2233 0.12011 0.11753 -0.0274 0.0015 1.0000
19.000 1.2014 0.12937 0.12693 -0.0327 0.0016 1.0000
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Polar data table (+)
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