S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9026 (9.5%) (s9026-il) Reynolds number: 200,000 Max Cl/Cd: 44.28 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9026-il-200000.txt Download as CSV file: xf-s9026-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.5562 0.12940 0.12595 0.0156 1.0000 0.0741
-12.000 -0.8774 0.06960 0.06569 -0.0231 1.0000 0.0351
-11.750 -0.8990 0.06399 0.05991 -0.0273 1.0000 0.0350
-11.250 -0.9386 0.05549 0.05104 -0.0291 1.0000 0.0347
-11.000 -0.9584 0.05211 0.04744 -0.0270 1.0000 0.0348
-10.500 -0.9851 0.04325 0.03787 -0.0232 1.0000 0.0352
-10.250 -0.9860 0.03899 0.03330 -0.0217 1.0000 0.0360
-10.000 -0.9727 0.03729 0.03156 -0.0208 1.0000 0.0377
-9.750 -0.9582 0.03581 0.02995 -0.0197 1.0000 0.0395
-9.500 -0.9456 0.03356 0.02738 -0.0183 1.0000 0.0409
-9.250 -0.9313 0.03124 0.02471 -0.0169 1.0000 0.0421
-9.000 -0.9139 0.02968 0.02283 -0.0156 1.0000 0.0439
-8.750 -0.8971 0.02736 0.02018 -0.0143 1.0000 0.0456
-8.500 -0.8778 0.02520 0.01793 -0.0134 1.0000 0.0477
-8.250 -0.8565 0.02393 0.01657 -0.0125 1.0000 0.0499
-8.000 -0.8348 0.02273 0.01521 -0.0115 1.0000 0.0527
-7.750 -0.8121 0.02192 0.01417 -0.0106 1.0000 0.0558
-7.500 -0.7918 0.02017 0.01246 -0.0096 1.0000 0.0603
-7.250 -0.7695 0.01929 0.01152 -0.0086 1.0000 0.0653
-7.000 -0.7484 0.01810 0.01030 -0.0075 1.0000 0.0714
-6.750 -0.7258 0.01746 0.00960 -0.0066 1.0000 0.0796
-6.500 -0.7044 0.01661 0.00879 -0.0056 1.0000 0.0893
-6.250 -0.6826 0.01586 0.00805 -0.0045 1.0000 0.0998
-6.000 -0.6605 0.01521 0.00741 -0.0035 1.0000 0.1119
-5.750 -0.6384 0.01460 0.00686 -0.0025 1.0000 0.1264
-5.500 -0.6163 0.01405 0.00637 -0.0015 1.0000 0.1440
-5.250 -0.5942 0.01351 0.00588 -0.0005 1.0000 0.1652
-5.000 -0.5725 0.01296 0.00545 0.0006 1.0000 0.1896
-4.750 -0.5508 0.01244 0.00507 0.0017 1.0000 0.2169
-4.500 -0.5289 0.01198 0.00473 0.0027 1.0000 0.2481
-4.250 -0.5071 0.01153 0.00443 0.0038 1.0000 0.2824
-4.000 -0.4854 0.01113 0.00418 0.0049 1.0000 0.3191
-3.750 -0.4638 0.01076 0.00396 0.0060 1.0000 0.3568
-3.500 -0.4423 0.01042 0.00379 0.0072 1.0000 0.3978
-3.250 -0.4213 0.01010 0.00364 0.0085 1.0000 0.4413
-3.000 -0.4005 0.00980 0.00354 0.0098 1.0000 0.4859
-2.750 -0.3801 0.00954 0.00347 0.0113 1.0000 0.5313
-2.500 -0.3598 0.00933 0.00344 0.0128 1.0000 0.5754
-2.250 -0.3399 0.00915 0.00344 0.0144 1.0000 0.6193
-2.000 -0.3204 0.00903 0.00349 0.0161 1.0000 0.6624
-1.750 -0.3016 0.00895 0.00358 0.0179 1.0000 0.7049
-1.500 -0.2751 0.00892 0.00372 0.0181 0.9970 0.7491
-1.250 -0.2324 0.00890 0.00385 0.0154 0.9873 0.7946
-1.000 -0.1895 0.00888 0.00396 0.0129 0.9772 0.8342
-0.750 -0.1438 0.00888 0.00403 0.0099 0.9680 0.8677
-0.500 -0.0985 0.00888 0.00409 0.0071 0.9576 0.8966
-0.250 -0.0497 0.00891 0.00415 0.0037 0.9473 0.9184
0.000 0.0000 0.00892 0.00417 0.0000 0.9353 0.9353
0.250 0.0497 0.00891 0.00415 -0.0037 0.9183 0.9472
0.500 0.0985 0.00888 0.00409 -0.0071 0.8965 0.9576
0.750 0.1439 0.00888 0.00403 -0.0099 0.8678 0.9680
1.000 0.1895 0.00888 0.00396 -0.0129 0.8341 0.9771
1.250 0.2324 0.00890 0.00386 -0.0154 0.7948 0.9873
1.500 0.2751 0.00892 0.00372 -0.0181 0.7490 0.9970
1.750 0.3017 0.00895 0.00358 -0.0179 0.7047 1.0000
2.000 0.3206 0.00903 0.00349 -0.0161 0.6623 1.0000
2.250 0.3401 0.00916 0.00344 -0.0144 0.6191 1.0000
2.500 0.3600 0.00933 0.00344 -0.0128 0.5752 1.0000
2.750 0.3802 0.00955 0.00347 -0.0113 0.5311 1.0000
3.000 0.4007 0.00980 0.00354 -0.0099 0.4859 1.0000
3.250 0.4214 0.01010 0.00364 -0.0085 0.4411 1.0000
3.500 0.4425 0.01042 0.00379 -0.0073 0.3978 1.0000
3.750 0.4639 0.01076 0.00396 -0.0061 0.3567 1.0000
4.000 0.4856 0.01113 0.00418 -0.0049 0.3191 1.0000
4.250 0.5073 0.01153 0.00443 -0.0038 0.2824 1.0000
4.500 0.5290 0.01198 0.00473 -0.0027 0.2481 1.0000
4.750 0.5509 0.01244 0.00507 -0.0017 0.2168 1.0000
5.000 0.5727 0.01296 0.00546 -0.0006 0.1895 1.0000
5.250 0.5943 0.01352 0.00588 0.0004 0.1651 1.0000
5.500 0.6164 0.01405 0.00637 0.0015 0.1440 1.0000
5.750 0.6385 0.01460 0.00686 0.0025 0.1264 1.0000
6.000 0.6606 0.01520 0.00741 0.0035 0.1119 1.0000
6.250 0.6827 0.01586 0.00805 0.0045 0.0998 1.0000
6.500 0.7044 0.01661 0.00879 0.0055 0.0893 1.0000
6.750 0.7258 0.01746 0.00961 0.0066 0.0796 1.0000
7.000 0.7484 0.01810 0.01030 0.0075 0.0713 1.0000
7.250 0.7695 0.01929 0.01152 0.0086 0.0653 1.0000
7.500 0.7918 0.02017 0.01246 0.0096 0.0602 1.0000
7.750 0.8120 0.02189 0.01415 0.0106 0.0558 1.0000
8.000 0.8347 0.02271 0.01520 0.0116 0.0526 1.0000
8.250 0.8564 0.02392 0.01655 0.0125 0.0499 1.0000
8.500 0.8776 0.02521 0.01793 0.0134 0.0477 1.0000
8.750 0.8970 0.02736 0.02017 0.0143 0.0456 1.0000
9.000 0.9137 0.02971 0.02285 0.0156 0.0439 1.0000
9.250 0.9311 0.03123 0.02471 0.0169 0.0422 1.0000
9.500 0.9454 0.03354 0.02736 0.0183 0.0408 1.0000
9.750 0.9582 0.03575 0.02989 0.0197 0.0394 1.0000
10.000 0.9721 0.03740 0.03169 0.0208 0.0378 1.0000
10.250 0.9857 0.03899 0.03331 0.0217 0.0361 1.0000
10.500 0.9851 0.04321 0.03783 0.0233 0.0352 1.0000
11.000 0.9589 0.05209 0.04741 0.0270 0.0348 1.0000
11.250 0.9390 0.05572 0.05126 0.0291 0.0348 1.0000
11.500 0.7253 0.10013 0.09649 -0.0029 0.0488 1.0000
11.750 0.7621 0.09253 0.08894 0.0023 0.0432 1.0000
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Polar data table (+)
Polar graphs
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