S8036 (16%) (s8036-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8036 (16%) (s8036-il) Reynolds number: 100,000 Max Cl/Cd: 48.25 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8036-il-100000.txt Download as CSV file: xf-s8036-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: S8036 (16%)
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
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4006 0.11883 0.11361 -0.0394 1.0000 0.1349
-11.500 -0.3906 0.09127 0.08653 -0.0574 1.0000 0.0902
-11.250 -0.5034 0.08591 0.08083 -0.0607 1.0000 0.0798
-11.000 -0.4598 0.09273 0.08770 -0.0529 1.0000 0.0936
-10.750 -0.6642 0.06884 0.06326 -0.0642 1.0000 0.0677
-10.500 -0.6467 0.06479 0.05926 -0.0640 1.0000 0.0653
-10.250 -0.6677 0.06215 0.05657 -0.0602 1.0000 0.0644
-10.000 -0.6952 0.05989 0.05425 -0.0545 1.0000 0.0636
-9.750 -0.7216 0.05732 0.05156 -0.0489 1.0000 0.0622
-9.500 -0.7545 0.05487 0.04890 -0.0419 1.0000 0.0607
-9.250 -0.8164 0.05352 0.04686 -0.0298 1.0000 0.0581
-9.000 -0.8253 0.05167 0.04488 -0.0254 1.0000 0.0577
-8.750 -0.8332 0.04945 0.04251 -0.0211 1.0000 0.0574
-8.500 -0.8391 0.04734 0.04021 -0.0170 1.0000 0.0572
-8.250 -0.8337 0.04479 0.03734 -0.0148 0.9980 0.0570
-8.000 -0.8093 0.04170 0.03360 -0.0157 0.9903 0.0577
-7.750 -0.7772 0.03879 0.03061 -0.0180 0.9846 0.0600
-7.500 -0.7467 0.03694 0.02860 -0.0194 0.9775 0.0630
-7.250 -0.7111 0.03467 0.02590 -0.0212 0.9721 0.0654
-7.000 -0.6807 0.03257 0.02360 -0.0220 0.9649 0.0690
-6.750 -0.6406 0.03120 0.02212 -0.0248 0.9599 0.0763
-6.500 -0.6123 0.02967 0.02065 -0.0253 0.9522 0.0829
-6.250 -0.5737 0.02822 0.01923 -0.0277 0.9473 0.0946
-6.000 -0.5487 0.02709 0.01818 -0.0276 0.9391 0.1081
-5.750 -0.5151 0.02588 0.01701 -0.0290 0.9332 0.1309
-5.500 -0.4975 0.02475 0.01617 -0.0278 0.9249 0.1583
-5.250 -0.4759 0.02332 0.01518 -0.0272 0.9180 0.2115
-5.000 -0.4715 0.02192 0.01454 -0.0237 0.9089 0.3070
-4.750 -0.4631 0.02079 0.01449 -0.0200 0.9014 0.4854
-4.500 -0.4492 0.02097 0.01490 -0.0166 0.8932 0.5750
-4.250 -0.4268 0.02130 0.01522 -0.0148 0.8858 0.6291
-4.000 -0.3861 0.02171 0.01559 -0.0157 0.8821 0.6711
-3.750 -0.3783 0.02218 0.01603 -0.0115 0.8720 0.6945
-3.500 -0.3407 0.02254 0.01631 -0.0121 0.8673 0.7224
-3.250 -0.2917 0.02291 0.01659 -0.0144 0.8647 0.7488
-3.000 -0.2891 0.02340 0.01706 -0.0095 0.8541 0.7653
-2.750 -0.2473 0.02366 0.01722 -0.0108 0.8501 0.7871
-2.500 -0.1913 0.02400 0.01744 -0.0145 0.8478 0.8073
-2.250 -0.1858 0.02453 0.01795 -0.0101 0.8380 0.8231
-2.000 -0.1161 0.02503 0.01832 -0.0165 0.8353 0.8357
-1.750 -0.0543 0.02511 0.01826 -0.0221 0.8325 0.8460
-1.500 0.0179 0.02514 0.01813 -0.0297 0.8303 0.8531
-1.250 0.0288 0.02550 0.01847 -0.0271 0.8205 0.8641
-1.000 0.0937 0.02548 0.01833 -0.0337 0.8167 0.8700
-0.750 0.1414 0.02521 0.01795 -0.0373 0.8128 0.8784
-0.500 0.1895 0.02555 0.01825 -0.0415 0.8053 0.8836
-0.250 0.2126 0.02548 0.01812 -0.0409 0.7983 0.8945
0.000 0.2844 0.02519 0.01774 -0.0488 0.7949 0.8974
0.250 0.3097 0.02560 0.01816 -0.0491 0.7853 0.9059
0.500 0.3483 0.02539 0.01789 -0.0512 0.7795 0.9133
0.750 0.3921 0.02547 0.01796 -0.0546 0.7725 0.9193
1.000 0.4137 0.02556 0.01804 -0.0540 0.7642 0.9288
1.250 0.4721 0.02514 0.01757 -0.0595 0.7595 0.9327
1.500 0.4860 0.02562 0.01809 -0.0580 0.7486 0.9431
1.750 0.5403 0.02516 0.01759 -0.0627 0.7429 0.9476
2.000 0.5639 0.02548 0.01797 -0.0629 0.7323 0.9569
2.250 0.6135 0.02499 0.01745 -0.0668 0.7258 0.9620
2.500 0.6397 0.02523 0.01775 -0.0673 0.7150 0.9712
2.750 0.6915 0.02458 0.01706 -0.0716 0.7078 0.9761
3.000 0.7230 0.02462 0.01718 -0.0730 0.6960 0.9845
3.250 0.7679 0.02409 0.01663 -0.0762 0.6866 0.9910
3.500 0.8106 0.02354 0.01610 -0.0792 0.6751 0.9978
3.750 0.8293 0.02346 0.01607 -0.0781 0.6632 1.0000
4.000 0.8531 0.02295 0.01550 -0.0770 0.6544 1.0000
4.250 0.8596 0.02302 0.01563 -0.0737 0.6423 1.0000
4.500 0.8703 0.02294 0.01558 -0.0708 0.6313 1.0000
4.750 0.8940 0.02239 0.01497 -0.0697 0.6219 1.0000
5.000 0.8975 0.02247 0.01511 -0.0657 0.6093 1.0000
5.250 0.9082 0.02232 0.01499 -0.0626 0.5977 1.0000
5.500 0.9300 0.02184 0.01445 -0.0611 0.5868 1.0000
5.750 0.9388 0.02172 0.01434 -0.0575 0.5736 1.0000
6.000 0.9473 0.02164 0.01429 -0.0539 0.5597 1.0000
6.250 0.9593 0.02149 0.01413 -0.0508 0.5454 1.0000
6.500 0.9724 0.02131 0.01394 -0.0477 0.5299 1.0000
6.750 0.9850 0.02118 0.01378 -0.0446 0.5130 1.0000
7.000 0.9974 0.02108 0.01365 -0.0414 0.4947 1.0000
7.250 1.0101 0.02103 0.01353 -0.0383 0.4751 1.0000
7.500 1.0190 0.02112 0.01355 -0.0345 0.4534 1.0000
7.750 1.0248 0.02136 0.01371 -0.0304 0.4297 1.0000
8.000 1.0316 0.02166 0.01387 -0.0264 0.4053 1.0000
8.250 1.0346 0.02213 0.01422 -0.0219 0.3802 1.0000
8.500 1.0379 0.02272 0.01462 -0.0176 0.3559 1.0000
8.750 1.0391 0.02344 0.01519 -0.0131 0.3328 1.0000
9.000 1.0412 0.02419 0.01573 -0.0089 0.3125 1.0000
9.250 1.0440 0.02502 0.01640 -0.0049 0.2936 1.0000
9.500 1.0481 0.02591 0.01717 -0.0012 0.2762 1.0000
9.750 1.0549 0.02685 0.01799 0.0018 0.2604 1.0000
10.000 1.0658 0.02785 0.01884 0.0041 0.2460 1.0000
10.250 1.0751 0.02883 0.01978 0.0065 0.2331 1.0000
10.500 1.0844 0.02988 0.02085 0.0089 0.2213 1.0000
10.750 1.0984 0.03099 0.02190 0.0104 0.2108 1.0000
11.000 1.1227 0.03212 0.02283 0.0105 0.2003 1.0000
11.250 1.1262 0.03324 0.02415 0.0135 0.1927 1.0000
11.500 1.1507 0.03445 0.02522 0.0135 0.1839 1.0000
11.750 1.1554 0.03566 0.02662 0.0161 0.1775 1.0000
12.000 1.1869 0.03697 0.02774 0.0152 0.1695 1.0000
12.250 1.1850 0.03829 0.02934 0.0185 0.1647 1.0000
12.500 1.1990 0.03952 0.03061 0.0197 0.1590 1.0000
12.750 1.2199 0.04111 0.03220 0.0200 0.1532 1.0000
13.000 1.2179 0.04267 0.03400 0.0228 0.1492 1.0000
13.250 1.2285 0.04404 0.03542 0.0242 0.1444 1.0000
13.500 1.2507 0.04584 0.03721 0.0242 0.1396 1.0000
13.750 1.2410 0.04781 0.03947 0.0273 0.1368 1.0000
14.000 1.2379 0.04980 0.04167 0.0294 0.1336 1.0000
14.250 1.2454 0.05152 0.04346 0.0307 0.1301 1.0000
14.500 1.2647 0.05366 0.04557 0.0308 0.1260 1.0000
14.750 1.2444 0.05646 0.04869 0.0335 0.1247 1.0000
15.000 1.2234 0.05972 0.05224 0.0356 0.1231 1.0000
15.250 1.2029 0.06331 0.05609 0.0370 0.1215 1.0000
15.500 1.1815 0.06736 0.06038 0.0379 0.1202 1.0000
15.750 1.1577 0.07193 0.06516 0.0382 0.1190 1.0000
16.000 1.1097 0.07922 0.07275 0.0373 0.1193 1.0000
16.250 0.9777 0.09941 0.09335 0.0292 0.1239 1.0000
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Polar data table (+)
Polar graphs
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