SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 200,000 Max Cl/Cd: 80.44 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd6080-il-200000-n5.txt Download as CSV file: xf-sd6080-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3265 0.08917 0.08580 -0.0339 1.0000 0.0265
-8.000 -0.3249 0.08606 0.08276 -0.0353 1.0000 0.0269
-7.750 -0.3260 0.08302 0.07979 -0.0362 1.0000 0.0270
-7.250 -0.3101 0.06805 0.06486 -0.0547 0.9632 0.0179
-7.000 -0.2898 0.06480 0.06157 -0.0587 0.9506 0.0166
-6.750 -0.2708 0.05925 0.05594 -0.0663 0.9353 0.0157
-6.250 -0.2426 0.03935 0.03536 -0.0823 0.9035 0.0129
-6.000 -0.2269 0.03438 0.02999 -0.0840 0.8915 0.0127
-5.750 -0.2093 0.02951 0.02457 -0.0850 0.8811 0.0126
-5.500 -0.1890 0.02576 0.02022 -0.0851 0.8719 0.0126
-5.250 -0.1664 0.02278 0.01666 -0.0849 0.8622 0.0127
-5.000 -0.1420 0.02067 0.01402 -0.0844 0.8541 0.0130
-4.750 -0.1175 0.01917 0.01226 -0.0842 0.8452 0.0139
-4.500 -0.0919 0.01832 0.01122 -0.0839 0.8369 0.0152
-4.250 -0.0660 0.01708 0.00970 -0.0834 0.8289 0.0157
-4.000 -0.0399 0.01599 0.00840 -0.0829 0.8206 0.0162
-3.750 -0.0137 0.01511 0.00734 -0.0824 0.8130 0.0167
-3.500 0.0128 0.01439 0.00647 -0.0820 0.8046 0.0174
-3.250 0.0390 0.01371 0.00569 -0.0816 0.7973 0.0186
-3.000 0.0660 0.01326 0.00516 -0.0814 0.7888 0.0208
-2.750 0.0928 0.01285 0.00466 -0.0811 0.7817 0.0253
-2.500 0.1200 0.01239 0.00417 -0.0808 0.7733 0.0340
-2.250 0.1471 0.01198 0.00377 -0.0806 0.7661 0.0620
-2.000 0.1738 0.01155 0.00357 -0.0805 0.7578 0.1204
-1.750 0.2002 0.01111 0.00340 -0.0804 0.7506 0.2051
-1.500 0.2269 0.01077 0.00326 -0.0803 0.7426 0.2832
-1.250 0.2532 0.01042 0.00315 -0.0801 0.7354 0.3801
-1.000 0.2783 0.00998 0.00311 -0.0796 0.7275 0.5125
-0.750 0.3009 0.00948 0.00309 -0.0783 0.7204 0.6710
-0.500 0.3224 0.00903 0.00307 -0.0761 0.7129 0.8477
-0.250 0.3691 0.00886 0.00288 -0.0796 0.7056 1.0000
0.000 0.3961 0.00893 0.00281 -0.0794 0.6977 1.0000
0.250 0.4232 0.00902 0.00277 -0.0792 0.6901 1.0000
0.500 0.4503 0.00910 0.00274 -0.0790 0.6823 1.0000
0.750 0.4774 0.00919 0.00274 -0.0788 0.6744 1.0000
1.000 0.5045 0.00928 0.00273 -0.0786 0.6665 1.0000
1.250 0.5317 0.00938 0.00276 -0.0784 0.6579 1.0000
1.750 0.5858 0.00959 0.00283 -0.0780 0.6400 1.0000
2.000 0.6128 0.00970 0.00288 -0.0778 0.6309 1.0000
2.250 0.6397 0.00981 0.00293 -0.0775 0.6217 1.0000
2.500 0.6666 0.00993 0.00303 -0.0773 0.6114 1.0000
2.750 0.6935 0.01005 0.00312 -0.0771 0.6013 1.0000
3.000 0.7202 0.01019 0.00320 -0.0768 0.5908 1.0000
3.250 0.7468 0.01032 0.00332 -0.0766 0.5790 1.0000
3.500 0.7734 0.01046 0.00347 -0.0763 0.5667 1.0000
3.750 0.7998 0.01062 0.00360 -0.0760 0.5539 1.0000
4.000 0.8261 0.01078 0.00375 -0.0757 0.5404 1.0000
4.250 0.8522 0.01095 0.00393 -0.0754 0.5261 1.0000
4.500 0.8781 0.01115 0.00411 -0.0750 0.5106 1.0000
4.750 0.9037 0.01136 0.00430 -0.0746 0.4936 1.0000
5.250 0.9540 0.01186 0.00477 -0.0737 0.4546 1.0000
5.500 0.9783 0.01218 0.00504 -0.0732 0.4323 1.0000
5.750 1.0023 0.01252 0.00534 -0.0726 0.4073 1.0000
6.000 1.0256 0.01292 0.00570 -0.0720 0.3808 1.0000
6.250 1.0483 0.01338 0.00609 -0.0712 0.3527 1.0000
6.500 1.0702 0.01390 0.00652 -0.0704 0.3228 1.0000
6.750 1.0913 0.01449 0.00701 -0.0696 0.2918 1.0000
7.000 1.1112 0.01519 0.00759 -0.0686 0.2585 1.0000
7.250 1.1296 0.01600 0.00822 -0.0675 0.2198 1.0000
7.500 1.1477 0.01684 0.00889 -0.0663 0.1846 1.0000
7.750 1.1660 0.01764 0.00957 -0.0652 0.1566 1.0000
8.000 1.1838 0.01845 0.01029 -0.0641 0.1316 1.0000
8.250 1.2014 0.01927 0.01105 -0.0629 0.1103 1.0000
8.500 1.2176 0.02016 0.01187 -0.0615 0.0881 1.0000
8.750 1.2327 0.02112 0.01274 -0.0601 0.0686 1.0000
9.000 1.2453 0.02222 0.01374 -0.0583 0.0486 1.0000
9.250 1.2559 0.02339 0.01484 -0.0563 0.0328 1.0000
9.500 1.2639 0.02458 0.01601 -0.0538 0.0240 1.0000
9.750 1.2730 0.02569 0.01721 -0.0516 0.0201 1.0000
10.000 1.2802 0.02699 0.01856 -0.0494 0.0180 1.0000
10.250 1.2887 0.02823 0.01994 -0.0474 0.0168 1.0000
10.500 1.2964 0.02957 0.02141 -0.0456 0.0160 1.0000
10.750 1.3027 0.03109 0.02305 -0.0439 0.0153 1.0000
11.000 1.3077 0.03275 0.02485 -0.0423 0.0147 1.0000
11.250 1.3104 0.03472 0.02692 -0.0408 0.0141 1.0000
11.500 1.3105 0.03699 0.02930 -0.0394 0.0136 1.0000
11.750 1.3145 0.03902 0.03151 -0.0383 0.0132 1.0000
12.000 1.3176 0.04122 0.03385 -0.0375 0.0127 1.0000
12.250 1.3191 0.04366 0.03643 -0.0367 0.0124 1.0000
12.500 1.3201 0.04625 0.03916 -0.0361 0.0121 1.0000
12.750 1.3203 0.04901 0.04207 -0.0357 0.0119 1.0000
13.000 1.3197 0.05196 0.04515 -0.0354 0.0117 1.0000
13.250 1.3189 0.05503 0.04836 -0.0353 0.0114 1.0000
13.500 1.3181 0.05817 0.05164 -0.0353 0.0113 1.0000
13.750 1.3163 0.06154 0.05515 -0.0355 0.0111 1.0000
14.000 1.3143 0.06503 0.05877 -0.0359 0.0109 1.0000
14.250 1.3118 0.06872 0.06260 -0.0365 0.0108 1.0000
14.500 1.3088 0.07259 0.06663 -0.0372 0.0106 1.0000
14.750 1.3057 0.07660 0.07078 -0.0381 0.0106 1.0000
15.000 1.3018 0.08085 0.07518 -0.0392 0.0104 1.0000
15.250 1.2973 0.08530 0.07978 -0.0405 0.0104 1.0000
15.500 1.2919 0.09003 0.08466 -0.0421 0.0102 1.0000
15.750 1.2858 0.09506 0.08986 -0.0439 0.0102 1.0000
16.000 1.2780 0.10048 0.09545 -0.0461 0.0101 1.0000
16.250 1.2698 0.10619 0.10134 -0.0487 0.0101 1.0000
16.500 1.2597 0.11245 0.10778 -0.0517 0.0100 1.0000
16.750 1.2490 0.11908 0.11458 -0.0553 0.0099 1.0000
17.000 1.2372 0.12626 0.12196 -0.0594 0.0099 1.0000
17.250 1.2254 0.13365 0.12954 -0.0639 0.0099 1.0000
17.500 1.2133 0.14142 0.13748 -0.0687 0.0099 1.0000
17.750 1.2000 0.14982 0.14605 -0.0741 0.0099 1.0000
18.000 1.1867 0.15859 0.15498 -0.0798 0.0099 1.0000
18.250 1.1732 0.16780 0.16435 -0.0858 0.0100 1.0000
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