S9037 (9%) (s9037-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 50,000 Max Cl/Cd: 39.83 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9037-il-50000-n5.txt Download as CSV file: xf-s9037-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2712 0.09842 0.09215 -0.0326 1.0000 0.1073
-8.500 -0.2689 0.09516 0.08894 -0.0325 1.0000 0.1085
-8.250 -0.2693 0.09206 0.08592 -0.0325 1.0000 0.1090
-8.000 -0.2718 0.08905 0.08300 -0.0325 1.0000 0.1090
-7.750 -0.2811 0.08317 0.07711 -0.0351 1.0000 0.0608
-7.250 -0.3629 0.08767 0.08143 -0.0352 1.0000 0.0650
-7.000 -0.3695 0.08277 0.07655 -0.0400 1.0000 0.0499
-6.750 -0.3681 0.08005 0.07391 -0.0377 1.0000 0.0489
-6.500 -0.3692 0.07723 0.07116 -0.0368 1.0000 0.0477
-6.250 -0.3710 0.07423 0.06821 -0.0367 1.0000 0.0466
-6.000 -0.3721 0.07091 0.06492 -0.0371 1.0000 0.0454
-5.750 -0.3712 0.06736 0.06136 -0.0378 1.0000 0.0440
-5.500 -0.3679 0.06329 0.05722 -0.0393 1.0000 0.0425
-5.250 -0.3607 0.05835 0.05210 -0.0416 1.0000 0.0406
-5.000 -0.3457 0.05256 0.04569 -0.0449 1.0000 0.0382
-4.750 -0.3334 0.04908 0.04200 -0.0452 1.0000 0.0380
-4.500 -0.3181 0.04559 0.03822 -0.0457 1.0000 0.0378
-4.250 -0.2914 0.04178 0.03396 -0.0480 0.9968 0.0376
-4.000 -0.2549 0.03782 0.02930 -0.0514 0.9907 0.0378
-3.750 -0.2186 0.03444 0.02539 -0.0543 0.9847 0.0392
-3.500 -0.1845 0.03244 0.02312 -0.0566 0.9778 0.0434
-3.250 -0.1462 0.03019 0.02026 -0.0587 0.9718 0.0478
-3.000 -0.1110 0.02822 0.01782 -0.0598 0.9651 0.0511
-2.750 -0.0746 0.02689 0.01625 -0.0616 0.9584 0.0611
-2.500 -0.0407 0.02562 0.01481 -0.0626 0.9509 0.0735
-2.250 -0.0030 0.02446 0.01356 -0.0643 0.9441 0.1008
-2.000 0.0314 0.02332 0.01260 -0.0658 0.9359 0.1604
-1.750 0.0684 0.02188 0.01205 -0.0682 0.9293 0.3397
-1.500 0.0894 0.02048 0.01199 -0.0662 0.9203 0.6477
-1.250 0.1443 0.01991 0.01145 -0.0700 0.9144 1.0000
-1.000 0.1772 0.02007 0.01118 -0.0711 0.9033 1.0000
-0.750 0.2120 0.02023 0.01095 -0.0726 0.8930 1.0000
-0.500 0.2515 0.02035 0.01074 -0.0747 0.8845 1.0000
-0.250 0.2831 0.02049 0.01063 -0.0754 0.8732 1.0000
0.000 0.3136 0.02064 0.01054 -0.0758 0.8616 1.0000
0.250 0.3449 0.02076 0.01048 -0.0764 0.8502 1.0000
0.500 0.3777 0.02085 0.01040 -0.0771 0.8394 1.0000
0.750 0.4116 0.02089 0.01028 -0.0778 0.8291 1.0000
1.000 0.4399 0.02101 0.01030 -0.0777 0.8164 1.0000
1.250 0.4684 0.02113 0.01032 -0.0775 0.8036 1.0000
1.500 0.4970 0.02123 0.01034 -0.0774 0.7909 1.0000
1.750 0.5255 0.02132 0.01037 -0.0771 0.7780 1.0000
2.000 0.5539 0.02140 0.01040 -0.0768 0.7649 1.0000
2.250 0.5822 0.02147 0.01043 -0.0764 0.7514 1.0000
2.500 0.6100 0.02154 0.01049 -0.0759 0.7375 1.0000
2.750 0.6376 0.02161 0.01054 -0.0754 0.7231 1.0000
3.000 0.6647 0.02169 0.01062 -0.0748 0.7082 1.0000
3.250 0.6917 0.02178 0.01071 -0.0741 0.6929 1.0000
3.500 0.7185 0.02188 0.01085 -0.0734 0.6772 1.0000
3.750 0.7453 0.02198 0.01095 -0.0726 0.6613 1.0000
4.000 0.7723 0.02208 0.01106 -0.0719 0.6450 1.0000
4.250 0.7967 0.02230 0.01131 -0.0709 0.6267 1.0000
4.500 0.8214 0.02251 0.01161 -0.0699 0.6079 1.0000
4.750 0.8470 0.02268 0.01180 -0.0690 0.5894 1.0000
5.000 0.8709 0.02296 0.01211 -0.0679 0.5695 1.0000
5.250 0.8948 0.02325 0.01244 -0.0669 0.5493 1.0000
5.500 0.9192 0.02354 0.01279 -0.0659 0.5294 1.0000
5.750 0.9416 0.02395 0.01327 -0.0647 0.5078 1.0000
6.000 0.9648 0.02432 0.01366 -0.0636 0.4868 1.0000
6.250 0.9861 0.02481 0.01421 -0.0623 0.4642 1.0000
6.500 1.0076 0.02530 0.01478 -0.0611 0.4420 1.0000
6.750 1.0284 0.02586 0.01539 -0.0598 0.4197 1.0000
7.000 1.0484 0.02650 0.01609 -0.0585 0.3972 1.0000
7.250 1.0682 0.02715 0.01677 -0.0571 0.3753 1.0000
7.500 1.0864 0.02793 0.01764 -0.0557 0.3526 1.0000
7.750 1.1045 0.02871 0.01848 -0.0542 0.3311 1.0000
8.000 1.1207 0.02960 0.01947 -0.0526 0.3084 1.0000
8.250 1.1365 0.03054 0.02045 -0.0510 0.2873 1.0000
8.500 1.1508 0.03157 0.02155 -0.0493 0.2661 1.0000
8.750 1.1648 0.03266 0.02265 -0.0476 0.2471 1.0000
9.000 1.1772 0.03388 0.02400 -0.0458 0.2277 1.0000
9.250 1.1890 0.03516 0.02541 -0.0440 0.2103 1.0000
9.500 1.1990 0.03652 0.02681 -0.0421 0.1939 1.0000
9.750 1.2080 0.03798 0.02831 -0.0401 0.1791 1.0000
10.000 1.2146 0.03951 0.02991 -0.0380 0.1652 1.0000
10.250 1.2196 0.04119 0.03168 -0.0359 0.1520 1.0000
10.500 1.2245 0.04303 0.03367 -0.0339 0.1399 1.0000
10.750 1.2277 0.04502 0.03581 -0.0321 0.1287 1.0000
11.000 1.2320 0.04718 0.03811 -0.0305 0.1191 1.0000
11.250 1.2356 0.04935 0.04030 -0.0290 0.1109 1.0000
11.500 1.2357 0.05191 0.04316 -0.0277 0.1024 1.0000
11.750 1.2360 0.05460 0.04600 -0.0266 0.0953 1.0000
12.000 1.2373 0.05742 0.04900 -0.0257 0.0891 1.0000
12.250 1.2365 0.06054 0.05228 -0.0250 0.0836 1.0000
12.500 1.2308 0.06413 0.05613 -0.0247 0.0785 1.0000
12.750 1.2303 0.06705 0.05899 -0.0244 0.0738 1.0000
13.000 1.2202 0.07188 0.06425 -0.0249 0.0707 1.0000
13.250 1.2095 0.07677 0.06943 -0.0259 0.0679 1.0000
13.500 1.2008 0.08130 0.07410 -0.0271 0.0649 1.0000
13.750 1.1961 0.08532 0.07812 -0.0280 0.0615 1.0000
14.000 1.1775 0.09217 0.08528 -0.0310 0.0607 1.0000
14.250 1.1567 0.09983 0.09320 -0.0348 0.0602 1.0000
14.500 1.1345 0.10843 0.10202 -0.0394 0.0603 1.0000
14.750 1.1102 0.11818 0.11194 -0.0451 0.0608 1.0000
15.000 1.0854 0.12899 0.12285 -0.0515 0.0615 1.0000
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Polar data table (+)
Polar graphs
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