S8052 (11.88%) (s8052-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8052 (11.88%) (s8052-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.27 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8052-il-1000000.txt Download as CSV file: xf-s8052-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4485 0.08595 0.08446 -0.0256 1.0000 0.0156
-10.750 -0.4682 0.07614 0.07467 -0.0300 1.0000 0.0160
-9.500 -0.7769 0.02767 0.02381 -0.0443 0.9758 0.0103
-9.250 -0.7488 0.02505 0.02101 -0.0462 0.9531 0.0099
-9.000 -0.7335 0.02301 0.01867 -0.0449 0.9244 0.0099
-8.750 -0.7183 0.02139 0.01678 -0.0432 0.9030 0.0099
-8.500 -0.6998 0.02022 0.01539 -0.0419 0.8868 0.0099
-8.250 -0.6789 0.01935 0.01435 -0.0409 0.8737 0.0100
-8.000 -0.6586 0.01805 0.01285 -0.0398 0.8625 0.0100
-7.750 -0.6372 0.01693 0.01158 -0.0389 0.8522 0.0100
-7.500 -0.6147 0.01599 0.01051 -0.0381 0.8429 0.0100
-7.250 -0.5915 0.01525 0.00965 -0.0374 0.8347 0.0101
-7.000 -0.5684 0.01440 0.00870 -0.0366 0.8267 0.0102
-6.750 -0.5479 0.01322 0.00740 -0.0355 0.8197 0.0105
-6.500 -0.5250 0.01243 0.00654 -0.0348 0.8130 0.0108
-6.250 -0.5005 0.01194 0.00597 -0.0342 0.8070 0.0111
-6.000 -0.4751 0.01152 0.00552 -0.0338 0.8016 0.0115
-5.750 -0.4493 0.01115 0.00510 -0.0335 0.7960 0.0119
-5.500 -0.4235 0.01081 0.00469 -0.0331 0.7908 0.0123
-5.250 -0.3971 0.01048 0.00432 -0.0328 0.7860 0.0127
-5.000 -0.3705 0.01019 0.00398 -0.0326 0.7811 0.0131
-4.750 -0.3438 0.00994 0.00367 -0.0323 0.7765 0.0134
-4.500 -0.3174 0.00957 0.00325 -0.0320 0.7719 0.0146
-4.250 -0.2903 0.00932 0.00299 -0.0318 0.7671 0.0163
-4.000 -0.2634 0.00906 0.00272 -0.0316 0.7625 0.0205
-3.750 -0.2381 0.00856 0.00240 -0.0312 0.7583 0.0606
-3.500 -0.2118 0.00816 0.00220 -0.0310 0.7540 0.1048
-3.250 -0.1854 0.00781 0.00202 -0.0309 0.7498 0.1513
-3.000 -0.1593 0.00748 0.00186 -0.0307 0.7455 0.2049
-2.750 -0.1331 0.00709 0.00171 -0.0305 0.7411 0.2734
-2.500 -0.1072 0.00666 0.00157 -0.0303 0.7364 0.3543
-2.250 -0.0817 0.00622 0.00144 -0.0300 0.7319 0.4478
-2.000 -0.0561 0.00583 0.00136 -0.0297 0.7276 0.5434
-1.750 -0.0294 0.00560 0.00133 -0.0295 0.7226 0.6108
-1.500 -0.0016 0.00552 0.00131 -0.0293 0.7174 0.6428
-1.250 0.0266 0.00549 0.00129 -0.0293 0.7121 0.6629
-1.000 0.0551 0.00545 0.00127 -0.0293 0.7060 0.6792
-0.750 0.0832 0.00545 0.00125 -0.0292 0.6998 0.6931
-0.500 0.1118 0.00542 0.00124 -0.0292 0.6936 0.7049
-0.250 0.1402 0.00541 0.00122 -0.0292 0.6866 0.7155
0.000 0.1687 0.00541 0.00122 -0.0292 0.6799 0.7261
0.250 0.1971 0.00540 0.00121 -0.0292 0.6727 0.7358
0.500 0.2256 0.00541 0.00121 -0.0292 0.6645 0.7449
0.750 0.2537 0.00542 0.00121 -0.0292 0.6544 0.7537
1.000 0.2822 0.00541 0.00121 -0.0292 0.6447 0.7620
1.250 0.3105 0.00543 0.00122 -0.0292 0.6344 0.7704
1.500 0.3386 0.00545 0.00123 -0.0292 0.6210 0.7785
1.750 0.3666 0.00549 0.00125 -0.0291 0.6063 0.7872
2.000 0.3943 0.00554 0.00128 -0.0290 0.5891 0.7955
2.250 0.4217 0.00564 0.00132 -0.0289 0.5674 0.8048
2.500 0.4486 0.00574 0.00139 -0.0286 0.5438 0.8142
2.750 0.4753 0.00588 0.00147 -0.0284 0.5200 0.8239
3.000 0.5021 0.00603 0.00155 -0.0282 0.4937 0.8337
3.250 0.5282 0.00621 0.00166 -0.0279 0.4633 0.8429
3.500 0.5539 0.00645 0.00179 -0.0275 0.4287 0.8526
3.750 0.5791 0.00671 0.00193 -0.0271 0.3898 0.8636
4.000 0.6041 0.00695 0.00208 -0.0266 0.3573 0.8755
4.250 0.6290 0.00717 0.00223 -0.0261 0.3287 0.8891
4.500 0.6532 0.00741 0.00241 -0.0254 0.2998 0.9061
4.750 0.6768 0.00763 0.00258 -0.0246 0.2736 0.9275
5.000 0.7033 0.00787 0.00277 -0.0244 0.2507 0.9532
5.250 0.7377 0.00816 0.00298 -0.0260 0.2269 0.9734
5.500 0.7734 0.00848 0.00320 -0.0280 0.2048 0.9887
5.750 0.8095 0.00878 0.00342 -0.0301 0.1863 0.9985
6.000 0.8350 0.00905 0.00362 -0.0299 0.1723 1.0000
6.250 0.8583 0.00931 0.00383 -0.0291 0.1603 1.0000
6.500 0.8818 0.00960 0.00405 -0.0285 0.1488 1.0000
6.750 0.9060 0.00984 0.00426 -0.0279 0.1395 1.0000
7.000 0.9303 0.01010 0.00450 -0.0274 0.1311 1.0000
7.500 0.9786 0.01066 0.00499 -0.0264 0.1141 1.0000
7.750 1.0025 0.01096 0.00527 -0.0258 0.1051 1.0000
8.000 1.0257 0.01133 0.00558 -0.0252 0.0947 1.0000
8.250 1.0492 0.01165 0.00587 -0.0247 0.0868 1.0000
8.500 1.0724 0.01200 0.00620 -0.0240 0.0791 1.0000
8.750 1.0944 0.01244 0.00659 -0.0233 0.0706 1.0000
9.000 1.1172 0.01279 0.00693 -0.0226 0.0647 1.0000
9.250 1.1389 0.01322 0.00734 -0.0218 0.0580 1.0000
9.500 1.1608 0.01362 0.00772 -0.0211 0.0532 1.0000
9.750 1.1815 0.01409 0.00817 -0.0201 0.0480 1.0000
10.000 1.2032 0.01447 0.00858 -0.0193 0.0452 1.0000
10.250 1.2228 0.01497 0.00906 -0.0183 0.0417 1.0000
10.500 1.2420 0.01547 0.00958 -0.0171 0.0388 1.0000
10.750 1.2623 0.01586 0.01001 -0.0161 0.0374 1.0000
11.000 1.2809 0.01632 0.01049 -0.0150 0.0354 1.0000
11.250 1.2962 0.01687 0.01103 -0.0132 0.0332 1.0000
11.500 1.3074 0.01753 0.01174 -0.0108 0.0312 1.0000
11.750 1.3237 0.01793 0.01219 -0.0093 0.0306 1.0000
12.000 1.3387 0.01842 0.01274 -0.0077 0.0297 1.0000
12.250 1.3529 0.01899 0.01334 -0.0060 0.0285 1.0000
12.500 1.3657 0.01965 0.01402 -0.0044 0.0270 1.0000
12.750 1.3766 0.02048 0.01487 -0.0026 0.0256 1.0000
13.000 1.3878 0.02131 0.01576 -0.0011 0.0244 1.0000
13.250 1.4021 0.02198 0.01649 0.0001 0.0238 1.0000
13.500 1.4152 0.02275 0.01731 0.0013 0.0230 1.0000
13.750 1.4268 0.02365 0.01826 0.0026 0.0221 1.0000
14.000 1.4377 0.02464 0.01927 0.0037 0.0207 1.0000
14.250 1.4452 0.02592 0.02058 0.0050 0.0191 1.0000
14.500 1.4572 0.02689 0.02162 0.0060 0.0186 1.0000
14.750 1.4679 0.02798 0.02275 0.0068 0.0166 1.0000
15.000 1.4735 0.02953 0.02431 0.0079 0.0147 1.0000
15.250 1.4789 0.03114 0.02597 0.0088 0.0121 1.0000
15.500 1.4817 0.03303 0.02790 0.0097 0.0102 1.0000
15.750 1.4759 0.03580 0.03069 0.0106 0.0073 1.0000
16.000 1.4789 0.03784 0.03281 0.0111 0.0071 1.0000
16.250 1.4742 0.04072 0.03577 0.0115 0.0062 1.0000
16.500 1.4718 0.04351 0.03866 0.0116 0.0058 1.0000
16.750 1.4679 0.04660 0.04185 0.0114 0.0055 1.0000
17.000 1.4650 0.04975 0.04511 0.0110 0.0054 1.0000
17.250 1.4571 0.05369 0.04916 0.0101 0.0051 1.0000
17.500 1.4471 0.05816 0.05375 0.0088 0.0049 1.0000
17.750 1.4400 0.06245 0.05815 0.0072 0.0049 1.0000
18.000 1.4291 0.06751 0.06334 0.0052 0.0049 1.0000
18.250 1.4142 0.07342 0.06939 0.0025 0.0048 1.0000
18.500 1.3940 0.08048 0.07661 -0.0009 0.0047 1.0000
18.750 1.3780 0.08710 0.08336 -0.0043 0.0047 1.0000
19.000 1.3544 0.09531 0.09173 -0.0087 0.0047 1.0000
19.250 1.3310 0.10373 0.10030 -0.0133 0.0048 1.0000
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Polar data table (+)
Polar graphs
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