SG6041 (sg6041-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SG6041 (sg6041-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.47 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6041-il-1000000.txt Download as CSV file: xf-sg6041-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SG6041
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3600 0.08074 0.07921 -0.0382 1.0000 0.0116
-9.500 -0.3675 0.07662 0.07511 -0.0385 1.0000 0.0117
-9.250 -0.3776 0.07270 0.07123 -0.0382 1.0000 0.0118
-8.250 -0.5593 0.02677 0.02357 -0.0699 0.9818 0.0080
-8.000 -0.5335 0.02544 0.02204 -0.0704 0.9784 0.0078
-7.750 -0.5167 0.02003 0.01606 -0.0711 0.9751 0.0073
-7.500 -0.4898 0.01750 0.01314 -0.0719 0.9731 0.0075
-7.250 -0.4601 0.01614 0.01154 -0.0727 0.9715 0.0076
-7.000 -0.4368 0.01533 0.01057 -0.0720 0.9659 0.0077
-6.750 -0.4143 0.01316 0.00816 -0.0715 0.9615 0.0082
-6.500 -0.3860 0.01245 0.00739 -0.0718 0.9585 0.0086
-6.250 -0.3608 0.01200 0.00689 -0.0714 0.9534 0.0090
-6.000 -0.3355 0.01149 0.00632 -0.0709 0.9483 0.0095
-5.750 -0.3089 0.01091 0.00566 -0.0707 0.9442 0.0097
-5.500 -0.2842 0.01044 0.00513 -0.0701 0.9388 0.0100
-5.250 -0.2587 0.01008 0.00471 -0.0696 0.9336 0.0104
-5.000 -0.2334 0.00949 0.00403 -0.0691 0.9290 0.0112
-4.750 -0.2084 0.00915 0.00368 -0.0686 0.9234 0.0125
-4.500 -0.1823 0.00887 0.00336 -0.0681 0.9182 0.0136
-4.250 -0.1562 0.00849 0.00292 -0.0677 0.9134 0.0154
-4.000 -0.1303 0.00827 0.00268 -0.0673 0.9079 0.0182
-3.750 -0.1045 0.00792 0.00237 -0.0668 0.9026 0.0278
-3.500 -0.0779 0.00770 0.00218 -0.0665 0.8977 0.0423
-3.250 -0.0517 0.00750 0.00205 -0.0662 0.8918 0.0571
-3.000 -0.0249 0.00733 0.00189 -0.0659 0.8863 0.0728
-2.750 0.0014 0.00712 0.00177 -0.0657 0.8806 0.0986
-2.500 0.0270 0.00681 0.00163 -0.0653 0.8744 0.1510
-2.250 0.0518 0.00636 0.00148 -0.0649 0.8685 0.2507
-2.000 0.0741 0.00565 0.00133 -0.0641 0.8615 0.4205
-1.750 0.0968 0.00507 0.00123 -0.0632 0.8550 0.5848
-1.500 0.1222 0.00486 0.00122 -0.0627 0.8479 0.6534
-1.250 0.1490 0.00480 0.00119 -0.0623 0.8407 0.6883
-1.000 0.1758 0.00474 0.00117 -0.0619 0.8327 0.7143
-0.500 0.2301 0.00470 0.00113 -0.0614 0.8157 0.7493
-0.250 0.2572 0.00469 0.00112 -0.0611 0.8059 0.7638
0.000 0.2837 0.00468 0.00111 -0.0606 0.7945 0.7815
0.250 0.3100 0.00468 0.00112 -0.0601 0.7818 0.7996
0.500 0.3365 0.00469 0.00113 -0.0596 0.7678 0.8137
1.000 0.3887 0.00478 0.00114 -0.0586 0.7316 0.8377
1.250 0.4139 0.00485 0.00116 -0.0579 0.7085 0.8471
1.500 0.4395 0.00494 0.00119 -0.0573 0.6833 0.8558
1.750 0.4645 0.00506 0.00123 -0.0567 0.6563 0.8649
2.000 0.4886 0.00521 0.00129 -0.0558 0.6237 0.8742
2.250 0.5129 0.00538 0.00136 -0.0550 0.5919 0.8847
2.500 0.5364 0.00556 0.00144 -0.0541 0.5570 0.8965
3.000 0.5809 0.00605 0.00167 -0.0517 0.4712 0.9264
3.250 0.6038 0.00633 0.00181 -0.0507 0.4260 0.9456
3.500 0.6328 0.00664 0.00197 -0.0511 0.3827 0.9642
3.750 0.6664 0.00697 0.00214 -0.0526 0.3417 0.9782
4.000 0.7006 0.00735 0.00232 -0.0543 0.2996 0.9890
4.250 0.7350 0.00771 0.00252 -0.0561 0.2631 0.9976
4.500 0.7608 0.00801 0.00269 -0.0560 0.2359 1.0000
4.750 0.7820 0.00827 0.00286 -0.0547 0.2135 1.0000
5.000 0.8038 0.00857 0.00305 -0.0536 0.1917 1.0000
5.250 0.8264 0.00885 0.00325 -0.0527 0.1725 1.0000
5.500 0.8493 0.00913 0.00345 -0.0519 0.1549 1.0000
5.750 0.8725 0.00941 0.00367 -0.0511 0.1401 1.0000
6.000 0.8955 0.00972 0.00389 -0.0503 0.1247 1.0000
6.250 0.9187 0.01003 0.00414 -0.0495 0.1110 1.0000
6.500 0.9422 0.01031 0.00438 -0.0488 0.1005 1.0000
6.750 0.9655 0.01061 0.00464 -0.0480 0.0911 1.0000
7.000 0.9886 0.01094 0.00493 -0.0473 0.0823 1.0000
7.250 1.0122 0.01121 0.00520 -0.0466 0.0755 1.0000
7.500 1.0348 0.01157 0.00552 -0.0458 0.0679 1.0000
7.750 1.0584 0.01184 0.00579 -0.0451 0.0639 1.0000
8.000 1.0806 0.01222 0.00615 -0.0442 0.0580 1.0000
8.250 1.1038 0.01251 0.00647 -0.0435 0.0548 1.0000
8.500 1.1263 0.01284 0.00680 -0.0427 0.0507 1.0000
8.750 1.1476 0.01327 0.00721 -0.0417 0.0457 1.0000
9.000 1.1704 0.01356 0.00753 -0.0410 0.0428 1.0000
9.250 1.1909 0.01402 0.00797 -0.0399 0.0381 1.0000
9.500 1.2124 0.01439 0.00838 -0.0389 0.0350 1.0000
9.750 1.2328 0.01483 0.00881 -0.0378 0.0319 1.0000
10.000 1.2510 0.01542 0.00941 -0.0363 0.0284 1.0000
10.250 1.2715 0.01579 0.00983 -0.0353 0.0270 1.0000
10.500 1.2901 0.01626 0.01033 -0.0339 0.0253 1.0000
10.750 1.3049 0.01689 0.01097 -0.0318 0.0232 1.0000
11.000 1.3190 0.01751 0.01166 -0.0296 0.0220 1.0000
11.250 1.3356 0.01797 0.01218 -0.0279 0.0213 1.0000
11.500 1.3514 0.01848 0.01274 -0.0262 0.0204 1.0000
11.750 1.3665 0.01903 0.01334 -0.0244 0.0194 1.0000
12.000 1.3790 0.01977 0.01411 -0.0223 0.0182 1.0000
12.250 1.3847 0.02092 0.01536 -0.0192 0.0170 1.0000
12.500 1.4020 0.02134 0.01583 -0.0180 0.0165 1.0000
12.750 1.4174 0.02188 0.01643 -0.0165 0.0157 1.0000
13.000 1.4299 0.02262 0.01723 -0.0147 0.0151 1.0000
13.250 1.4420 0.02339 0.01805 -0.0130 0.0145 1.0000
13.500 1.4500 0.02446 0.01916 -0.0109 0.0135 1.0000
13.750 1.4500 0.02609 0.02091 -0.0081 0.0129 1.0000
14.000 1.4632 0.02685 0.02176 -0.0068 0.0125 1.0000
14.250 1.4740 0.02780 0.02278 -0.0054 0.0122 1.0000
14.500 1.4829 0.02892 0.02398 -0.0039 0.0117 1.0000
14.750 1.4909 0.03013 0.02526 -0.0024 0.0113 1.0000
15.000 1.4974 0.03151 0.02672 -0.0010 0.0108 1.0000
15.250 1.5016 0.03313 0.02841 0.0003 0.0104 1.0000
15.500 1.4997 0.03534 0.03071 0.0018 0.0099 1.0000
15.750 1.4940 0.03804 0.03353 0.0031 0.0095 1.0000
16.000 1.4989 0.03988 0.03547 0.0037 0.0093 1.0000
16.250 1.5025 0.04192 0.03761 0.0042 0.0090 1.0000
16.500 1.5020 0.04450 0.04031 0.0044 0.0088 1.0000
16.750 1.5007 0.04733 0.04324 0.0044 0.0085 1.0000
17.000 1.4979 0.05047 0.04650 0.0040 0.0083 1.0000
17.250 1.4935 0.05405 0.05017 0.0032 0.0080 1.0000
17.500 1.4853 0.05836 0.05460 0.0019 0.0078 1.0000
17.750 1.4753 0.06319 0.05955 0.0001 0.0076 1.0000
18.000 1.4599 0.06919 0.06569 -0.0026 0.0074 1.0000
18.250 1.4392 0.07646 0.07311 -0.0062 0.0074 1.0000
18.500 1.4155 0.08464 0.08145 -0.0106 0.0073 1.0000
18.750 1.3883 0.09387 0.09086 -0.0156 0.0074 1.0000
19.000 1.3599 0.10358 0.10073 -0.0211 0.0075 1.0000
19.250 1.3286 0.11415 0.11147 -0.0271 0.0076 1.0000
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