S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 200,000 Max Cl/Cd: 66.06 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8052-il-200000.txt Download as CSV file: xf-s8052-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: S8052 (11.88%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4861 0.08976 0.08633 -0.0287 1.0000 0.0631
-9.500 -0.4963 0.08367 0.08030 -0.0335 1.0000 0.0655
-9.250 -0.5307 0.07364 0.07028 -0.0447 1.0000 0.0668
-9.000 -0.5695 0.06898 0.06552 -0.0473 1.0000 0.0674
-8.750 -0.6045 0.06690 0.06311 -0.0465 1.0000 0.0682
-8.500 -0.6153 0.06000 0.05617 -0.0466 1.0000 0.0695
-8.250 -0.6006 0.05665 0.05297 -0.0460 1.0000 0.0708
-8.000 -0.5982 0.05446 0.05082 -0.0440 1.0000 0.0720
-7.750 -0.6203 0.05364 0.05001 -0.0380 1.0000 0.0724
-7.500 -0.6248 0.03660 0.03106 -0.0391 0.9872 0.0353
-7.250 -0.5981 0.03159 0.02563 -0.0411 0.9818 0.0332
-7.000 -0.5696 0.02774 0.02121 -0.0421 0.9751 0.0316
-6.750 -0.5341 0.02489 0.01788 -0.0439 0.9713 0.0310
-6.500 -0.5000 0.02306 0.01582 -0.0454 0.9661 0.0316
-6.250 -0.4651 0.02179 0.01440 -0.0470 0.9607 0.0332
-6.000 -0.4277 0.02041 0.01286 -0.0489 0.9569 0.0347
-5.750 -0.3971 0.01921 0.01156 -0.0494 0.9500 0.0355
-5.500 -0.3663 0.01775 0.01007 -0.0501 0.9442 0.0371
-5.250 -0.3395 0.01675 0.00910 -0.0502 0.9373 0.0401
-5.000 -0.3130 0.01605 0.00833 -0.0500 0.9301 0.0443
-4.750 -0.2891 0.01521 0.00749 -0.0494 0.9232 0.0563
-4.500 -0.2724 0.01372 0.00658 -0.0478 0.9151 0.1429
-4.250 -0.2517 0.01292 0.00621 -0.0469 0.9084 0.2431
-4.000 -0.2325 0.01222 0.00598 -0.0457 0.9010 0.3518
-3.750 -0.2153 0.01145 0.00589 -0.0438 0.8950 0.4991
-3.500 -0.1957 0.01125 0.00606 -0.0418 0.8877 0.6044
-3.250 -0.1715 0.01126 0.00613 -0.0405 0.8825 0.6573
-3.000 -0.1479 0.01137 0.00625 -0.0392 0.8757 0.6938
-2.750 -0.1233 0.01146 0.00632 -0.0379 0.8698 0.7215
-2.500 -0.0985 0.01156 0.00637 -0.0367 0.8645 0.7450
-2.250 -0.0744 0.01167 0.00646 -0.0354 0.8576 0.7643
-2.000 -0.0494 0.01173 0.00648 -0.0342 0.8526 0.7822
-1.750 -0.0253 0.01183 0.00655 -0.0330 0.8459 0.7982
-1.500 -0.0007 0.01187 0.00656 -0.0318 0.8398 0.8129
-1.250 0.0239 0.01191 0.00656 -0.0305 0.8343 0.8269
-1.000 0.0477 0.01195 0.00658 -0.0293 0.8268 0.8403
-0.750 0.0727 0.01194 0.00651 -0.0280 0.8215 0.8531
-0.500 0.0962 0.01198 0.00655 -0.0269 0.8136 0.8660
-0.250 0.1215 0.01194 0.00648 -0.0257 0.8075 0.8772
0.000 0.1462 0.01195 0.00648 -0.0246 0.7996 0.8882
0.250 0.1722 0.01189 0.00638 -0.0236 0.7926 0.8994
0.500 0.1973 0.01187 0.00634 -0.0227 0.7841 0.9113
0.750 0.2280 0.01179 0.00622 -0.0226 0.7766 0.9206
1.000 0.2586 0.01176 0.00618 -0.0228 0.7669 0.9304
1.250 0.2903 0.01167 0.00602 -0.0230 0.7592 0.9403
1.500 0.3287 0.01162 0.00596 -0.0249 0.7483 0.9466
1.750 0.3626 0.01156 0.00587 -0.0259 0.7382 0.9555
2.000 0.4045 0.01144 0.00570 -0.0284 0.7285 0.9598
2.250 0.4438 0.01133 0.00558 -0.0306 0.7159 0.9660
2.500 0.4819 0.01122 0.00547 -0.0327 0.7027 0.9724
2.750 0.5218 0.01110 0.00535 -0.0351 0.6893 0.9786
3.000 0.5602 0.01098 0.00522 -0.0373 0.6745 0.9855
3.250 0.6000 0.01085 0.00509 -0.0398 0.6580 0.9924
3.500 0.6405 0.01070 0.00493 -0.0424 0.6393 0.9991
3.750 0.6601 0.01063 0.00486 -0.0412 0.6187 1.0000
4.000 0.6758 0.01059 0.00478 -0.0391 0.5968 1.0000
4.250 0.6913 0.01062 0.00475 -0.0369 0.5719 1.0000
4.500 0.7075 0.01074 0.00475 -0.0348 0.5429 1.0000
4.750 0.7247 0.01097 0.00482 -0.0329 0.5082 1.0000
5.000 0.7423 0.01131 0.00497 -0.0310 0.4696 1.0000
5.250 0.7600 0.01175 0.00520 -0.0293 0.4287 1.0000
5.500 0.7781 0.01225 0.00550 -0.0277 0.3879 1.0000
5.750 0.7966 0.01280 0.00585 -0.0262 0.3508 1.0000
6.000 0.8156 0.01337 0.00625 -0.0249 0.3178 1.0000
6.250 0.8349 0.01396 0.00670 -0.0236 0.2897 1.0000
6.500 0.8541 0.01458 0.00716 -0.0224 0.2663 1.0000
6.750 0.8746 0.01513 0.00765 -0.0214 0.2456 1.0000
7.000 0.8948 0.01570 0.00815 -0.0204 0.2275 1.0000
7.250 0.9149 0.01627 0.00866 -0.0193 0.2115 1.0000
7.500 0.9350 0.01685 0.00920 -0.0183 0.1969 1.0000
7.750 0.9550 0.01743 0.00975 -0.0173 0.1833 1.0000
8.000 0.9746 0.01804 0.01035 -0.0162 0.1705 1.0000
8.250 0.9935 0.01869 0.01097 -0.0151 0.1584 1.0000
8.500 1.0115 0.01940 0.01164 -0.0139 0.1472 1.0000
8.750 1.0291 0.02010 0.01231 -0.0126 0.1362 1.0000
9.000 1.0472 0.02074 0.01301 -0.0114 0.1258 1.0000
9.250 1.0636 0.02155 0.01384 -0.0100 0.1167 1.0000
9.500 1.0785 0.02246 0.01468 -0.0085 0.1086 1.0000
9.750 1.0944 0.02319 0.01552 -0.0069 0.1012 1.0000
10.000 1.1072 0.02430 0.01652 -0.0052 0.0948 1.0000
10.250 1.1213 0.02502 0.01740 -0.0034 0.0893 1.0000
10.500 1.1336 0.02597 0.01833 -0.0017 0.0844 1.0000
10.750 1.1488 0.02723 0.01966 -0.0004 0.0803 1.0000
11.000 1.1627 0.02824 0.02079 0.0011 0.0765 1.0000
11.250 1.1762 0.02932 0.02190 0.0024 0.0734 1.0000
11.500 1.1950 0.03105 0.02360 0.0030 0.0699 1.0000
11.750 1.2059 0.03216 0.02492 0.0046 0.0676 1.0000
12.000 1.2178 0.03346 0.02637 0.0059 0.0653 1.0000
12.250 1.2301 0.03480 0.02783 0.0071 0.0632 1.0000
12.500 1.2436 0.03624 0.02930 0.0081 0.0612 1.0000
12.750 1.2598 0.03879 0.03194 0.0086 0.0587 1.0000
13.000 1.2620 0.04025 0.03363 0.0104 0.0575 1.0000
13.250 1.2647 0.04197 0.03557 0.0118 0.0560 1.0000
13.500 1.2658 0.04363 0.03739 0.0131 0.0541 1.0000
13.750 1.2691 0.04558 0.03948 0.0140 0.0526 1.0000
14.000 1.2744 0.04693 0.04080 0.0146 0.0505 1.0000
14.250 1.2763 0.05013 0.04408 0.0152 0.0484 1.0000
14.500 1.2685 0.05250 0.04669 0.0157 0.0475 1.0000
14.750 1.2615 0.05531 0.04974 0.0159 0.0463 1.0000
15.000 1.2551 0.05841 0.05305 0.0157 0.0451 1.0000
15.250 1.2479 0.06174 0.05655 0.0151 0.0439 1.0000
15.500 1.2416 0.06518 0.06013 0.0143 0.0428 1.0000
15.750 1.2427 0.06765 0.06261 0.0135 0.0413 1.0000
16.000 1.2396 0.07116 0.06618 0.0126 0.0403 1.0000
16.500 1.2037 0.08300 0.07842 0.0076 0.0389 1.0000
16.750 1.1828 0.08994 0.08560 0.0038 0.0387 1.0000
17.000 1.1575 0.09825 0.09414 -0.0010 0.0387 1.0000
17.250 1.1281 0.10797 0.10407 -0.0070 0.0387 1.0000
17.500 1.0918 0.11982 0.11612 -0.0145 0.0391 1.0000
|
Polar data table (+)
Polar graphs
<< Back to S8052 (11.88%) (s8052-il)