SG6041 (sg6041-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: SG6041 (sg6041-il) Reynolds number: 100,000 Max Cl/Cd: 53.46 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sg6041-il-100000.txt Download as CSV file: xf-sg6041-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4237 0.10357 0.09848 -0.0331 1.0000 0.0927
-9.250 -0.4211 0.10054 0.09549 -0.0331 1.0000 0.0959
-9.000 -0.4274 0.09747 0.09250 -0.0346 1.0000 0.0997
-8.750 -0.4501 0.09472 0.08988 -0.0385 1.0000 0.1018
-8.500 -0.4794 0.09192 0.08723 -0.0414 1.0000 0.1023
-8.250 -0.5061 0.08949 0.08486 -0.0419 1.0000 0.1025
-8.000 -0.4503 0.08476 0.08011 -0.0350 1.0000 0.1083
-7.750 -0.4638 0.08220 0.07766 -0.0341 1.0000 0.1106
-7.500 -0.4849 0.07939 0.07493 -0.0339 1.0000 0.1128
-7.250 -0.5127 0.07668 0.07222 -0.0346 1.0000 0.1157
-7.000 -0.5508 0.07509 0.07033 -0.0350 1.0000 0.1175
-6.750 -0.5266 0.07009 0.06566 -0.0314 1.0000 0.1206
-6.500 -0.5255 0.06759 0.06318 -0.0293 1.0000 0.1245
-6.250 -0.5443 0.06450 0.05975 -0.0302 1.0000 0.1330
-6.000 -0.5333 0.06121 0.05665 -0.0274 1.0000 0.1365
-5.250 -0.5211 0.05255 0.04769 -0.0242 1.0000 0.1651
-5.000 -0.5130 0.04995 0.04498 -0.0231 1.0000 0.1795
-4.750 -0.4761 0.03718 0.03037 -0.0247 1.0000 0.0698
-4.500 -0.4537 0.03390 0.02600 -0.0227 1.0000 0.0615
-4.250 -0.4330 0.03131 0.02305 -0.0217 1.0000 0.0616
-4.000 -0.4107 0.02851 0.01986 -0.0208 1.0000 0.0622
-3.750 -0.3874 0.02630 0.01737 -0.0198 1.0000 0.0630
-3.500 -0.3646 0.02465 0.01557 -0.0189 1.0000 0.0655
-3.250 -0.3422 0.02366 0.01441 -0.0178 1.0000 0.0720
-3.000 -0.3193 0.02217 0.01285 -0.0168 1.0000 0.0786
-2.750 -0.2971 0.02119 0.01181 -0.0157 1.0000 0.0903
-2.500 -0.2758 0.02012 0.01090 -0.0147 1.0000 0.1085
-2.250 -0.2550 0.01920 0.01016 -0.0136 1.0000 0.1392
-2.000 -0.2347 0.01818 0.00955 -0.0126 1.0000 0.2005
-1.750 -0.2316 0.01582 0.00997 -0.0064 1.0000 0.7810
-1.500 -0.1930 0.01599 0.01031 -0.0059 1.0000 0.9560
-1.250 -0.1481 0.01622 0.01022 -0.0102 1.0000 1.0000
-1.000 -0.1313 0.01633 0.01011 -0.0094 0.9993 1.0000
-0.750 -0.0862 0.01689 0.01040 -0.0138 0.9909 1.0000
-0.500 -0.0415 0.01749 0.01077 -0.0181 0.9828 1.0000
-0.250 0.0005 0.01794 0.01103 -0.0217 0.9733 1.0000
0.000 0.0395 0.01832 0.01126 -0.0246 0.9633 1.0000
0.250 0.0818 0.01874 0.01156 -0.0281 0.9538 1.0000
0.500 0.1265 0.01912 0.01182 -0.0318 0.9443 1.0000
0.750 0.1635 0.01936 0.01198 -0.0341 0.9326 1.0000
1.000 0.2029 0.01958 0.01215 -0.0366 0.9213 1.0000
1.250 0.2484 0.01976 0.01229 -0.0401 0.9113 1.0000
1.500 0.2937 0.01981 0.01232 -0.0434 0.9004 1.0000
1.750 0.3321 0.01980 0.01231 -0.0453 0.8875 1.0000
2.000 0.3730 0.01969 0.01222 -0.0474 0.8749 1.0000
2.250 0.4181 0.01943 0.01201 -0.0501 0.8628 1.0000
2.500 0.4822 0.01869 0.01136 -0.0558 0.8550 1.0000
2.750 0.5230 0.01816 0.01089 -0.0572 0.8411 1.0000
3.000 0.5628 0.01755 0.01038 -0.0582 0.8266 1.0000
3.250 0.6014 0.01690 0.00980 -0.0589 0.8113 1.0000
3.500 0.6326 0.01636 0.00932 -0.0582 0.7922 1.0000
3.750 0.6632 0.01582 0.00886 -0.0574 0.7704 1.0000
4.000 0.6927 0.01533 0.00841 -0.0564 0.7455 1.0000
4.250 0.7210 0.01494 0.00802 -0.0552 0.7153 1.0000
4.500 0.7489 0.01467 0.00772 -0.0540 0.6788 1.0000
4.750 0.7731 0.01464 0.00757 -0.0523 0.6331 1.0000
5.000 0.7939 0.01485 0.00758 -0.0502 0.5788 1.0000
5.250 0.8122 0.01529 0.00771 -0.0478 0.5182 1.0000
5.500 0.8282 0.01595 0.00803 -0.0453 0.4568 1.0000
5.750 0.8431 0.01676 0.00849 -0.0428 0.3987 1.0000
6.000 0.8583 0.01767 0.00907 -0.0406 0.3483 1.0000
6.250 0.8743 0.01865 0.00972 -0.0386 0.3066 1.0000
6.500 0.8917 0.01961 0.01052 -0.0369 0.2712 1.0000
6.750 0.9104 0.02063 0.01135 -0.0354 0.2431 1.0000
7.000 0.9299 0.02169 0.01221 -0.0342 0.2196 1.0000
7.250 0.9505 0.02273 0.01323 -0.0331 0.1993 1.0000
7.500 0.9720 0.02384 0.01432 -0.0322 0.1824 1.0000
7.750 0.9935 0.02497 0.01543 -0.0313 0.1675 1.0000
8.000 1.0159 0.02623 0.01670 -0.0306 0.1547 1.0000
8.250 1.0383 0.02754 0.01801 -0.0299 0.1433 1.0000
8.500 1.0620 0.02900 0.01939 -0.0295 0.1329 1.0000
8.750 1.0807 0.03011 0.02074 -0.0281 0.1234 1.0000
9.000 1.1019 0.03182 0.02259 -0.0273 0.1150 1.0000
9.250 1.1241 0.03341 0.02412 -0.0268 0.1072 1.0000
9.500 1.1395 0.03517 0.02628 -0.0250 0.1004 1.0000
9.750 1.1599 0.03700 0.02818 -0.0242 0.0947 1.0000
10.000 1.1730 0.03963 0.03120 -0.0224 0.0903 1.0000
10.250 1.1844 0.04160 0.03350 -0.0203 0.0855 1.0000
10.500 1.2021 0.04372 0.03562 -0.0195 0.0814 1.0000
10.750 1.2065 0.04732 0.03963 -0.0171 0.0793 1.0000
11.000 1.2018 0.05039 0.04324 -0.0134 0.0778 1.0000
11.250 1.1935 0.05362 0.04691 -0.0098 0.0763 1.0000
11.500 1.1813 0.05684 0.05049 -0.0062 0.0751 1.0000
11.750 1.1638 0.06003 0.05397 -0.0023 0.0744 1.0000
12.000 1.1426 0.06354 0.05773 0.0009 0.0739 1.0000
12.250 1.1141 0.06801 0.06247 0.0032 0.0743 1.0000
12.500 1.0815 0.07335 0.06804 0.0038 0.0750 1.0000
12.750 1.0454 0.08013 0.07502 0.0023 0.0764 1.0000
13.000 1.0123 0.08787 0.08287 -0.0011 0.0778 1.0000
13.250 0.9838 0.09646 0.09153 -0.0055 0.0791 1.0000
13.500 0.9598 0.10562 0.10072 -0.0103 0.0799 1.0000
|
Polar data table (+)
Polar graphs
<< Back to SG6041 (sg6041-il)