S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 100,000 Max Cl/Cd: 34.65 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9026-il-100000-n5.txt Download as CSV file: xf-s9026-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9026 (9.5%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7856 0.09862 0.09342 0.0009 1.0000 0.0346
-12.250 -0.8226 0.08518 0.07998 -0.0080 1.0000 0.0340
-12.000 -0.8550 0.07425 0.06897 -0.0162 1.0000 0.0332
-11.750 -0.8856 0.06547 0.06001 -0.0231 1.0000 0.0327
-11.500 -0.9112 0.05913 0.05346 -0.0271 1.0000 0.0323
-11.250 -0.9326 0.05445 0.04854 -0.0283 1.0000 0.0324
-11.000 -0.9502 0.05084 0.04467 -0.0273 1.0000 0.0327
-10.750 -0.9623 0.04761 0.04109 -0.0255 1.0000 0.0335
-10.500 -0.9668 0.04445 0.03750 -0.0239 1.0000 0.0344
-10.250 -0.9642 0.04145 0.03417 -0.0224 1.0000 0.0353
-10.000 -0.9544 0.03912 0.03171 -0.0213 1.0000 0.0363
-9.750 -0.9422 0.03715 0.02956 -0.0201 1.0000 0.0374
-9.500 -0.9284 0.03523 0.02740 -0.0190 1.0000 0.0389
-9.250 -0.9131 0.03349 0.02541 -0.0179 1.0000 0.0410
-9.000 -0.8964 0.03176 0.02335 -0.0167 1.0000 0.0435
-8.750 -0.8788 0.02994 0.02131 -0.0156 1.0000 0.0457
-8.500 -0.8603 0.02849 0.01981 -0.0147 1.0000 0.0479
-8.250 -0.8409 0.02718 0.01839 -0.0137 1.0000 0.0508
-8.000 -0.8205 0.02595 0.01692 -0.0126 1.0000 0.0547
-7.750 -0.8010 0.02476 0.01569 -0.0117 1.0000 0.0591
-7.500 -0.7803 0.02377 0.01462 -0.0107 1.0000 0.0644
-7.250 -0.7597 0.02270 0.01345 -0.0097 1.0000 0.0699
-7.000 -0.7385 0.02187 0.01258 -0.0088 1.0000 0.0774
-6.750 -0.7174 0.02101 0.01170 -0.0078 1.0000 0.0857
-6.500 -0.6955 0.02025 0.01085 -0.0069 1.0000 0.0957
-6.250 -0.6736 0.01955 0.01011 -0.0060 1.0000 0.1073
-6.000 -0.6519 0.01885 0.00943 -0.0051 1.0000 0.1206
-5.750 -0.6299 0.01819 0.00879 -0.0041 1.0000 0.1355
-5.500 -0.6080 0.01755 0.00819 -0.0032 1.0000 0.1515
-5.250 -0.5861 0.01696 0.00766 -0.0023 1.0000 0.1709
-5.000 -0.5638 0.01643 0.00717 -0.0013 1.0000 0.1926
-4.750 -0.5418 0.01590 0.00673 -0.0003 1.0000 0.2164
-4.500 -0.5198 0.01541 0.00634 0.0007 1.0000 0.2440
-4.250 -0.4979 0.01495 0.00597 0.0017 1.0000 0.2748
-4.000 -0.4760 0.01453 0.00567 0.0028 1.0000 0.3084
-3.750 -0.4544 0.01411 0.00540 0.0039 1.0000 0.3440
-3.500 -0.4326 0.01374 0.00516 0.0050 1.0000 0.3809
-3.250 -0.4111 0.01339 0.00494 0.0062 1.0000 0.4185
-3.000 -0.3897 0.01307 0.00478 0.0075 1.0000 0.4575
-2.750 -0.3684 0.01278 0.00465 0.0088 1.0000 0.4978
-2.500 -0.3474 0.01252 0.00456 0.0102 1.0000 0.5391
-2.250 -0.3267 0.01230 0.00450 0.0117 1.0000 0.5817
-2.000 -0.3060 0.01212 0.00448 0.0132 1.0000 0.6238
-1.750 -0.2853 0.01198 0.00450 0.0148 1.0000 0.6651
-1.500 -0.2546 0.01191 0.00456 0.0143 0.9942 0.7086
-1.250 -0.2142 0.01188 0.00466 0.0121 0.9824 0.7525
-1.000 -0.1744 0.01186 0.00474 0.0102 0.9697 0.7932
-0.750 -0.1336 0.01185 0.00481 0.0082 0.9567 0.8287
-0.500 -0.0913 0.01185 0.00486 0.0059 0.9427 0.8595
-0.250 -0.0462 0.01185 0.00490 0.0031 0.9270 0.8858
0.000 0.0000 0.01186 0.00491 0.0000 0.9081 0.9081
0.250 0.0462 0.01185 0.00490 -0.0030 0.8858 0.9270
0.500 0.0913 0.01185 0.00486 -0.0059 0.8595 0.9427
0.750 0.1336 0.01185 0.00481 -0.0082 0.8287 0.9566
1.000 0.1743 0.01186 0.00474 -0.0102 0.7930 0.9696
1.250 0.2142 0.01188 0.00466 -0.0121 0.7524 0.9824
1.500 0.2545 0.01191 0.00456 -0.0143 0.7084 0.9941
1.750 0.2854 0.01198 0.00450 -0.0148 0.6650 1.0000
2.000 0.3061 0.01211 0.00448 -0.0132 0.6241 1.0000
2.250 0.3268 0.01230 0.00450 -0.0117 0.5817 1.0000
2.500 0.3476 0.01252 0.00456 -0.0102 0.5394 1.0000
2.750 0.3686 0.01278 0.00465 -0.0088 0.4980 1.0000
3.000 0.3898 0.01307 0.00478 -0.0075 0.4574 1.0000
3.250 0.4113 0.01339 0.00495 -0.0062 0.4186 1.0000
3.500 0.4328 0.01374 0.00516 -0.0050 0.3808 1.0000
3.750 0.4545 0.01411 0.00540 -0.0039 0.3440 1.0000
4.250 0.4980 0.01495 0.00597 -0.0017 0.2747 1.0000
4.500 0.5199 0.01541 0.00634 -0.0007 0.2439 1.0000
4.750 0.5419 0.01590 0.00673 0.0003 0.2163 1.0000
5.000 0.5638 0.01643 0.00717 0.0013 0.1926 1.0000
5.250 0.5862 0.01696 0.00766 0.0022 0.1709 1.0000
5.500 0.6081 0.01755 0.00819 0.0032 0.1515 1.0000
5.750 0.6299 0.01819 0.00879 0.0041 0.1355 1.0000
6.000 0.6519 0.01885 0.00943 0.0051 0.1206 1.0000
6.250 0.6736 0.01955 0.01011 0.0060 0.1074 1.0000
6.500 0.6955 0.02026 0.01085 0.0069 0.0958 1.0000
6.750 0.7174 0.02101 0.01169 0.0078 0.0856 1.0000
7.000 0.7385 0.02186 0.01257 0.0088 0.0774 1.0000
7.250 0.7596 0.02270 0.01345 0.0097 0.0698 1.0000
7.500 0.7802 0.02377 0.01462 0.0107 0.0644 1.0000
7.750 0.8009 0.02476 0.01569 0.0117 0.0591 1.0000
8.000 0.8204 0.02594 0.01691 0.0127 0.0546 1.0000
8.250 0.8408 0.02718 0.01838 0.0137 0.0507 1.0000
8.500 0.8602 0.02849 0.01981 0.0147 0.0479 1.0000
8.750 0.8786 0.02994 0.02132 0.0157 0.0457 1.0000
9.000 0.8962 0.03175 0.02333 0.0167 0.0436 1.0000
9.250 0.9129 0.03348 0.02540 0.0179 0.0410 1.0000
9.500 0.9282 0.03522 0.02739 0.0190 0.0388 1.0000
9.750 0.9420 0.03713 0.02952 0.0202 0.0374 1.0000
10.000 0.9542 0.03913 0.03172 0.0213 0.0363 1.0000
10.250 0.9640 0.04146 0.03418 0.0224 0.0353 1.0000
10.500 0.9668 0.04444 0.03748 0.0239 0.0344 1.0000
10.750 0.9624 0.04759 0.04107 0.0255 0.0335 1.0000
11.000 0.9504 0.05087 0.04469 0.0273 0.0329 1.0000
11.250 0.9326 0.05452 0.04861 0.0283 0.0325 1.0000
11.500 0.9110 0.05916 0.05349 0.0271 0.0323 1.0000
11.750 0.8855 0.06548 0.06002 0.0230 0.0325 1.0000
12.000 0.8554 0.07423 0.06895 0.0162 0.0332 1.0000
12.250 0.8202 0.08589 0.08070 0.0073 0.0340 1.0000
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Polar data table (+)
Polar graphs
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