S2091-101-83 (s2091-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: S2091-101-83 (s2091-il) Reynolds number: 500,000 Max Cl/Cd: 107.44 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s2091-il-500000.txt Download as CSV file: xf-s2091-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: S2091-101-83
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3234 0.09332 0.09113 -0.0304 1.0000 0.0216
-8.750 -0.3202 0.08985 0.08770 -0.0322 1.0000 0.0228
-8.000 -0.3261 0.07395 0.07195 -0.0455 0.9839 0.0246
-7.750 -0.3007 0.07227 0.07025 -0.0479 0.9731 0.0253
-7.500 -0.2827 0.06666 0.06461 -0.0566 0.9523 0.0255
-7.250 -0.2692 0.06401 0.06190 -0.0597 0.9329 0.0267
-7.000 -0.3175 0.03360 0.03065 -0.0827 0.8993 0.0187
-6.750 -0.3184 0.02149 0.01716 -0.0851 0.8869 0.0177
-6.500 -0.2964 0.01915 0.01436 -0.0847 0.8788 0.0183
-6.250 -0.2722 0.01753 0.01237 -0.0843 0.8706 0.0190
-6.000 -0.2464 0.01660 0.01113 -0.0839 0.8629 0.0196
-5.750 -0.2221 0.01493 0.00930 -0.0836 0.8550 0.0208
-5.500 -0.1954 0.01451 0.00880 -0.0834 0.8474 0.0222
-5.250 -0.1685 0.01397 0.00810 -0.0830 0.8395 0.0237
-5.000 -0.1422 0.01292 0.00689 -0.0827 0.8321 0.0251
-4.750 -0.1153 0.01240 0.00633 -0.0825 0.8242 0.0267
-4.500 -0.0879 0.01200 0.00583 -0.0822 0.8166 0.0287
-4.250 -0.0608 0.01140 0.00514 -0.0820 0.8087 0.0311
-4.000 -0.0333 0.01107 0.00478 -0.0818 0.8011 0.0336
-3.750 -0.0055 0.01078 0.00441 -0.0816 0.7930 0.0361
-3.500 0.0219 0.01032 0.00392 -0.0814 0.7854 0.0401
-3.250 0.0499 0.01010 0.00365 -0.0812 0.7772 0.0441
-3.000 0.0777 0.00975 0.00328 -0.0811 0.7692 0.0507
-2.750 0.1056 0.00947 0.00298 -0.0810 0.7610 0.0603
-2.500 0.1337 0.00924 0.00275 -0.0809 0.7526 0.0726
-2.250 0.1617 0.00906 0.00255 -0.0808 0.7443 0.0860
-2.000 0.1899 0.00888 0.00239 -0.0807 0.7354 0.1013
-1.750 0.2178 0.00873 0.00223 -0.0806 0.7272 0.1225
-1.500 0.2459 0.00848 0.00212 -0.0806 0.7177 0.1615
-1.250 0.2736 0.00818 0.00202 -0.0806 0.7091 0.2345
-1.000 0.3010 0.00783 0.00197 -0.0807 0.6997 0.3390
-0.750 0.3284 0.00752 0.00195 -0.0806 0.6903 0.4474
-0.500 0.3552 0.00725 0.00194 -0.0804 0.6813 0.5555
-0.250 0.3817 0.00695 0.00195 -0.0800 0.6710 0.6631
0.000 0.4048 0.00658 0.00198 -0.0786 0.6615 0.8027
0.250 0.4399 0.00626 0.00190 -0.0795 0.6512 1.0000
0.500 0.4680 0.00633 0.00188 -0.0794 0.6403 1.0000
0.750 0.4959 0.00641 0.00187 -0.0793 0.6298 1.0000
1.000 0.5237 0.00651 0.00186 -0.0792 0.6192 1.0000
1.250 0.5517 0.00659 0.00188 -0.0791 0.6078 1.0000
1.500 0.5796 0.00669 0.00190 -0.0790 0.5964 1.0000
1.750 0.6074 0.00680 0.00193 -0.0789 0.5850 1.0000
2.000 0.6350 0.00693 0.00197 -0.0788 0.5733 1.0000
2.250 0.6628 0.00704 0.00203 -0.0787 0.5608 1.0000
2.500 0.6905 0.00716 0.00209 -0.0786 0.5483 1.0000
2.750 0.7180 0.00729 0.00216 -0.0784 0.5356 1.0000
3.000 0.7455 0.00744 0.00225 -0.0783 0.5227 1.0000
3.250 0.7728 0.00760 0.00234 -0.0782 0.5096 1.0000
3.500 0.8000 0.00777 0.00245 -0.0780 0.4963 1.0000
3.750 0.8271 0.00795 0.00256 -0.0779 0.4825 1.0000
4.000 0.8542 0.00812 0.00270 -0.0777 0.4684 1.0000
4.250 0.8811 0.00831 0.00283 -0.0775 0.4541 1.0000
4.500 0.9079 0.00851 0.00299 -0.0774 0.4396 1.0000
4.750 0.9346 0.00872 0.00316 -0.0772 0.4249 1.0000
5.000 0.9610 0.00895 0.00334 -0.0770 0.4098 1.0000
5.250 0.9874 0.00919 0.00353 -0.0767 0.3947 1.0000
5.500 1.0135 0.00945 0.00374 -0.0765 0.3794 1.0000
5.750 1.0393 0.00972 0.00396 -0.0762 0.3636 1.0000
6.000 1.0650 0.01001 0.00420 -0.0759 0.3481 1.0000
6.250 1.0905 0.01031 0.00445 -0.0756 0.3326 1.0000
6.500 1.1156 0.01063 0.00473 -0.0753 0.3168 1.0000
7.000 1.1654 0.01131 0.00531 -0.0745 0.2856 1.0000
7.250 1.1899 0.01166 0.00564 -0.0741 0.2703 1.0000
7.500 1.2141 0.01204 0.00597 -0.0737 0.2554 1.0000
7.750 1.2380 0.01243 0.00633 -0.0732 0.2410 1.0000
8.000 1.2615 0.01284 0.00671 -0.0727 0.2268 1.0000
8.250 1.2846 0.01327 0.00710 -0.0721 0.2124 1.0000
8.500 1.3073 0.01373 0.00752 -0.0715 0.1981 1.0000
8.750 1.3295 0.01421 0.00797 -0.0708 0.1836 1.0000
9.000 1.3511 0.01471 0.00844 -0.0700 0.1690 1.0000
9.250 1.3719 0.01526 0.00895 -0.0692 0.1540 1.0000
9.500 1.3918 0.01585 0.00950 -0.0682 0.1390 1.0000
9.750 1.4106 0.01650 0.01010 -0.0671 0.1237 1.0000
10.000 1.4280 0.01721 0.01076 -0.0658 0.1092 1.0000
10.250 1.4440 0.01798 0.01147 -0.0644 0.0956 1.0000
10.500 1.4586 0.01878 0.01223 -0.0628 0.0838 1.0000
10.750 1.4704 0.01959 0.01301 -0.0607 0.0742 1.0000
11.000 1.4789 0.02048 0.01389 -0.0581 0.0663 1.0000
11.250 1.4873 0.02143 0.01485 -0.0558 0.0597 1.0000
11.500 1.4960 0.02241 0.01587 -0.0537 0.0544 1.0000
11.750 1.5029 0.02358 0.01705 -0.0516 0.0497 1.0000
12.000 1.5096 0.02483 0.01835 -0.0496 0.0458 1.0000
12.250 1.5173 0.02606 0.01964 -0.0480 0.0425 1.0000
12.500 1.5186 0.02787 0.02147 -0.0460 0.0392 1.0000
12.750 1.5262 0.02927 0.02297 -0.0447 0.0370 1.0000
13.000 1.5319 0.03089 0.02467 -0.0435 0.0346 1.0000
13.250 1.5318 0.03311 0.02692 -0.0422 0.0322 1.0000
13.500 1.5317 0.03545 0.02937 -0.0411 0.0307 1.0000
13.750 1.5377 0.03731 0.03133 -0.0405 0.0291 1.0000
14.000 1.5397 0.03962 0.03372 -0.0399 0.0276 1.0000
14.250 1.5370 0.04255 0.03671 -0.0395 0.0263 1.0000
14.500 1.5269 0.04644 0.04070 -0.0393 0.0252 1.0000
14.750 1.5289 0.04909 0.04348 -0.0393 0.0243 1.0000
15.000 1.5300 0.05194 0.04643 -0.0395 0.0232 1.0000
15.250 1.5279 0.05530 0.04991 -0.0399 0.0224 1.0000
15.500 1.5243 0.05899 0.05369 -0.0406 0.0216 1.0000
15.750 1.5159 0.06350 0.05829 -0.0417 0.0208 1.0000
16.000 1.5036 0.06870 0.06358 -0.0431 0.0202 1.0000
16.250 1.4952 0.07354 0.06855 -0.0446 0.0197 1.0000
16.500 1.4931 0.07758 0.07273 -0.0459 0.0191 1.0000
16.750 1.4888 0.08205 0.07731 -0.0475 0.0185 1.0000
17.000 1.4815 0.08710 0.08248 -0.0494 0.0181 1.0000
17.250 1.4752 0.09209 0.08758 -0.0515 0.0176 1.0000
17.500 1.4674 0.09743 0.09302 -0.0537 0.0171 1.0000
17.750 1.4583 0.10306 0.09874 -0.0562 0.0167 1.0000
18.000 1.4482 0.10893 0.10470 -0.0589 0.0163 1.0000
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Polar data table (+)
Polar graphs
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