S9037 (9%) (s9037-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 50,000 Max Cl/Cd: 34.71 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s9037-il-50000.txt Download as CSV file: xf-s9037-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: S9037 (9%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3640 0.10217 0.09588 -0.0258 1.0000 0.2042
-7.500 -0.3393 0.09658 0.09025 -0.0239 1.0000 0.2155
-7.250 -0.3714 0.09749 0.09144 -0.0235 1.0000 0.2186
-7.000 -0.3492 0.09245 0.08637 -0.0213 1.0000 0.2306
-6.750 -0.3515 0.08979 0.08383 -0.0195 1.0000 0.2376
-6.500 -0.3687 0.08900 0.08321 -0.0184 1.0000 0.2464
-6.250 -0.3614 0.08560 0.07988 -0.0156 1.0000 0.2557
-6.000 -0.3752 0.08396 0.07838 -0.0144 1.0000 0.2647
-5.750 -0.3912 0.08315 0.07768 -0.0142 1.0000 0.2763
-5.500 -0.3864 0.08004 0.07465 -0.0106 1.0000 0.2892
-5.250 -0.3863 0.07745 0.07214 -0.0078 1.0000 0.3013
-5.000 -0.3980 0.07595 0.07072 -0.0073 1.0000 0.3194
-4.750 -0.3987 0.07328 0.06815 -0.0045 1.0000 0.3359
-4.500 -0.3959 0.07057 0.06551 -0.0005 1.0000 0.3538
-3.750 -0.3030 0.04999 0.04334 -0.0412 1.0000 0.1613
-3.500 -0.2744 0.04426 0.03721 -0.0433 1.0000 0.1287
-3.250 -0.2433 0.03992 0.03210 -0.0457 1.0000 0.1167
-3.000 -0.2177 0.03696 0.02873 -0.0463 1.0000 0.1151
-2.750 -0.1899 0.03420 0.02546 -0.0469 1.0000 0.1135
-2.500 -0.1621 0.03181 0.02251 -0.0470 1.0000 0.1132
-2.250 -0.1358 0.02996 0.02019 -0.0469 1.0000 0.1211
-2.000 -0.1106 0.02853 0.01839 -0.0463 1.0000 0.1318
-1.750 -0.0871 0.02719 0.01704 -0.0458 1.0000 0.1515
-1.500 -0.0634 0.02601 0.01585 -0.0449 1.0000 0.1865
-1.250 -0.0357 0.02461 0.01478 -0.0448 1.0000 0.2742
-1.000 -0.0155 0.02078 0.01366 -0.0413 1.0000 1.0000
-0.750 0.0059 0.02128 0.01343 -0.0411 1.0000 1.0000
-0.500 0.0259 0.02183 0.01352 -0.0408 1.0000 1.0000
-0.250 0.0451 0.02243 0.01376 -0.0406 1.0000 1.0000
0.000 0.0640 0.02308 0.01410 -0.0405 1.0000 1.0000
0.250 0.0989 0.02411 0.01478 -0.0434 0.9928 1.0000
0.500 0.1479 0.02537 0.01570 -0.0488 0.9771 1.0000
0.750 0.1946 0.02654 0.01660 -0.0536 0.9613 1.0000
1.000 0.2403 0.02763 0.01746 -0.0580 0.9452 1.0000
1.250 0.2861 0.02866 0.01832 -0.0622 0.9292 1.0000
1.500 0.3274 0.02957 0.01908 -0.0655 0.9126 1.0000
1.750 0.3628 0.03037 0.01979 -0.0677 0.8951 1.0000
2.000 0.4005 0.03114 0.02050 -0.0701 0.8777 1.0000
2.250 0.4408 0.03184 0.02116 -0.0726 0.8606 1.0000
2.500 0.4834 0.03243 0.02173 -0.0753 0.8440 1.0000
2.750 0.5181 0.03302 0.02231 -0.0766 0.8263 1.0000
3.000 0.5496 0.03359 0.02291 -0.0774 0.8080 1.0000
3.250 0.5885 0.03395 0.02333 -0.0789 0.7906 1.0000
3.500 0.6317 0.03407 0.02352 -0.0807 0.7741 1.0000
3.750 0.6769 0.03394 0.02348 -0.0824 0.7582 1.0000
4.000 0.7001 0.03449 0.02414 -0.0814 0.7384 1.0000
4.250 0.7361 0.03440 0.02415 -0.0814 0.7208 1.0000
4.500 0.7765 0.03391 0.02378 -0.0815 0.7039 1.0000
4.750 0.8190 0.03313 0.02317 -0.0814 0.6875 1.0000
5.000 0.8410 0.03351 0.02366 -0.0798 0.6662 1.0000
5.250 0.8784 0.03285 0.02313 -0.0790 0.6477 1.0000
5.500 0.9144 0.03222 0.02260 -0.0779 0.6285 1.0000
5.750 0.9410 0.03220 0.02275 -0.0763 0.6063 1.0000
6.000 0.9730 0.03176 0.02240 -0.0748 0.5842 1.0000
6.250 1.0044 0.03136 0.02206 -0.0733 0.5608 1.0000
6.500 1.0285 0.03157 0.02241 -0.0715 0.5358 1.0000
6.750 1.0547 0.03170 0.02259 -0.0698 0.5104 1.0000
7.000 1.0812 0.03187 0.02278 -0.0681 0.4845 1.0000
7.250 1.1066 0.03215 0.02306 -0.0664 0.4576 1.0000
7.500 1.1308 0.03262 0.02355 -0.0647 0.4303 1.0000
7.750 1.1534 0.03323 0.02414 -0.0630 0.4026 1.0000
8.000 1.1740 0.03405 0.02495 -0.0611 0.3749 1.0000
8.250 1.1917 0.03516 0.02613 -0.0592 0.3482 1.0000
8.500 1.2085 0.03644 0.02749 -0.0572 0.3225 1.0000
8.750 1.2258 0.03783 0.02892 -0.0553 0.2978 1.0000
9.000 1.2452 0.03916 0.03024 -0.0537 0.2737 1.0000
9.250 1.2595 0.04085 0.03204 -0.0517 0.2514 1.0000
9.500 1.2741 0.04270 0.03395 -0.0497 0.2304 1.0000
9.750 1.2857 0.04477 0.03617 -0.0476 0.2116 1.0000
10.000 1.3067 0.04667 0.03788 -0.0465 0.1924 1.0000
10.250 1.3159 0.04937 0.04081 -0.0444 0.1782 1.0000
10.500 1.3238 0.05192 0.04354 -0.0422 0.1644 1.0000
10.750 1.3159 0.05567 0.04786 -0.0390 0.1575 1.0000
11.000 1.3204 0.05920 0.05163 -0.0371 0.1490 1.0000
11.250 1.3043 0.06320 0.05606 -0.0340 0.1450 1.0000
11.500 1.3076 0.06617 0.05910 -0.0321 0.1359 1.0000
11.750 1.2823 0.07041 0.06366 -0.0291 0.1352 1.0000
12.000 1.2548 0.07513 0.06861 -0.0271 0.1355 1.0000
12.250 1.2259 0.08063 0.07424 -0.0266 0.1362 1.0000
12.500 1.1975 0.08700 0.08075 -0.0276 0.1372 1.0000
12.750 1.1709 0.09422 0.08805 -0.0298 0.1381 1.0000
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Polar data table (+)
Polar graphs
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