S9037 (9%) (s9037-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9037 (9%) (s9037-il) Reynolds number: 200,000 Max Cl/Cd: 74.31 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9037-il-200000-n5.txt Download as CSV file: xf-s9037-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3339 0.08719 0.08383 -0.0339 1.0000 0.0244
-7.750 -0.3372 0.08454 0.08125 -0.0338 1.0000 0.0244
-7.250 -0.3607 0.08072 0.07761 -0.0303 1.0000 0.0245
-6.750 -0.2531 0.04656 0.04352 -0.0597 0.9681 0.0136
-6.500 -0.2948 0.05659 0.05329 -0.0639 0.9726 0.0135
-6.250 -0.2708 0.05054 0.04709 -0.0711 0.9647 0.0130
-6.000 -0.2440 0.04347 0.03975 -0.0781 0.9576 0.0123
-5.750 -0.2217 0.03633 0.03219 -0.0824 0.9482 0.0115
-5.500 -0.1981 0.02725 0.02208 -0.0852 0.9404 0.0104
-5.250 -0.1728 0.02402 0.01825 -0.0856 0.9325 0.0101
-5.000 -0.1448 0.02148 0.01522 -0.0861 0.9267 0.0102
-4.750 -0.1191 0.01957 0.01292 -0.0859 0.9189 0.0103
-4.500 -0.0902 0.01799 0.01106 -0.0862 0.9134 0.0105
-4.250 -0.0646 0.01685 0.00972 -0.0857 0.9050 0.0108
-4.000 -0.0364 0.01582 0.00852 -0.0856 0.8987 0.0113
-3.750 -0.0105 0.01498 0.00755 -0.0851 0.8899 0.0122
-3.500 0.0166 0.01421 0.00665 -0.0847 0.8821 0.0134
-3.250 0.0431 0.01361 0.00595 -0.0843 0.8734 0.0162
-3.000 0.0697 0.01317 0.00542 -0.0839 0.8642 0.0199
-2.750 0.0969 0.01253 0.00469 -0.0834 0.8561 0.0271
-2.500 0.1230 0.01198 0.00423 -0.0830 0.8462 0.0529
-2.250 0.1493 0.01148 0.00390 -0.0827 0.8367 0.1031
-2.000 0.1758 0.01103 0.00365 -0.0824 0.8276 0.1726
-1.750 0.2018 0.01063 0.00346 -0.0821 0.8171 0.2526
-1.500 0.2275 0.01022 0.00332 -0.0817 0.8064 0.3518
-1.250 0.2525 0.00978 0.00320 -0.0811 0.7958 0.4679
-1.000 0.2757 0.00928 0.00313 -0.0800 0.7852 0.6139
-0.500 0.3365 0.00850 0.00297 -0.0793 0.7628 0.9534
-0.250 0.3754 0.00848 0.00279 -0.0815 0.7509 1.0000
0.000 0.4011 0.00855 0.00271 -0.0809 0.7384 1.0000
0.250 0.4270 0.00862 0.00264 -0.0803 0.7252 1.0000
0.500 0.4529 0.00870 0.00259 -0.0798 0.7114 1.0000
0.750 0.4788 0.00880 0.00255 -0.0793 0.6971 1.0000
1.000 0.5047 0.00890 0.00254 -0.0788 0.6824 1.0000
1.250 0.5307 0.00901 0.00254 -0.0783 0.6677 1.0000
1.500 0.5567 0.00913 0.00256 -0.0778 0.6527 1.0000
1.750 0.5827 0.00927 0.00260 -0.0773 0.6374 1.0000
2.000 0.6086 0.00941 0.00265 -0.0768 0.6217 1.0000
2.250 0.6344 0.00957 0.00272 -0.0764 0.6050 1.0000
2.500 0.6599 0.00974 0.00279 -0.0758 0.5873 1.0000
2.750 0.6854 0.00992 0.00289 -0.0753 0.5680 1.0000
3.000 0.7108 0.01012 0.00300 -0.0748 0.5492 1.0000
3.250 0.7361 0.01033 0.00314 -0.0743 0.5313 1.0000
3.500 0.7614 0.01055 0.00329 -0.0738 0.5130 1.0000
3.750 0.7865 0.01078 0.00346 -0.0733 0.4937 1.0000
4.000 0.8112 0.01105 0.00364 -0.0727 0.4730 1.0000
4.250 0.8358 0.01132 0.00387 -0.0721 0.4518 1.0000
4.750 0.8846 0.01191 0.00434 -0.0709 0.4122 1.0000
5.000 0.9088 0.01223 0.00461 -0.0704 0.3927 1.0000
5.250 0.9328 0.01257 0.00492 -0.0697 0.3738 1.0000
5.500 0.9568 0.01291 0.00523 -0.0691 0.3543 1.0000
5.750 0.9802 0.01329 0.00556 -0.0685 0.3343 1.0000
6.000 1.0033 0.01369 0.00592 -0.0678 0.3127 1.0000
6.250 1.0259 0.01413 0.00632 -0.0670 0.2910 1.0000
6.500 1.0486 0.01457 0.00673 -0.0663 0.2707 1.0000
6.750 1.0709 0.01503 0.00717 -0.0655 0.2515 1.0000
7.000 1.0928 0.01553 0.00764 -0.0647 0.2330 1.0000
7.250 1.1145 0.01604 0.00815 -0.0639 0.2138 1.0000
7.500 1.1357 0.01658 0.00868 -0.0630 0.1960 1.0000
7.750 1.1560 0.01719 0.00926 -0.0620 0.1778 1.0000
8.000 1.1761 0.01781 0.00986 -0.0610 0.1591 1.0000
8.250 1.1956 0.01846 0.01049 -0.0600 0.1424 1.0000
8.500 1.2145 0.01915 0.01119 -0.0588 0.1275 1.0000
8.750 1.2327 0.01987 0.01191 -0.0576 0.1137 1.0000
9.000 1.2506 0.02059 0.01267 -0.0564 0.1017 1.0000
9.250 1.2677 0.02134 0.01346 -0.0550 0.0909 1.0000
9.500 1.2837 0.02215 0.01431 -0.0535 0.0804 1.0000
9.750 1.2980 0.02302 0.01521 -0.0518 0.0710 1.0000
10.000 1.3093 0.02396 0.01617 -0.0497 0.0629 1.0000
10.250 1.3213 0.02485 0.01718 -0.0477 0.0556 1.0000
10.500 1.3308 0.02591 0.01828 -0.0455 0.0483 1.0000
10.750 1.3391 0.02708 0.01944 -0.0434 0.0405 1.0000
11.000 1.3491 0.02816 0.02059 -0.0416 0.0335 1.0000
11.250 1.3564 0.02947 0.02194 -0.0397 0.0280 1.0000
11.500 1.3627 0.03090 0.02344 -0.0379 0.0239 1.0000
11.750 1.3679 0.03246 0.02511 -0.0361 0.0206 1.0000
12.000 1.3720 0.03419 0.02695 -0.0345 0.0173 1.0000
12.250 1.3731 0.03628 0.02913 -0.0329 0.0149 1.0000
12.500 1.3748 0.03840 0.03143 -0.0316 0.0131 1.0000
12.750 1.3735 0.04093 0.03407 -0.0305 0.0115 1.0000
13.000 1.3689 0.04396 0.03726 -0.0297 0.0104 1.0000
13.250 1.3659 0.04696 0.04045 -0.0292 0.0098 1.0000
13.500 1.3614 0.05030 0.04397 -0.0291 0.0091 1.0000
13.750 1.3554 0.05401 0.04784 -0.0294 0.0086 1.0000
14.000 1.3495 0.05791 0.05191 -0.0300 0.0083 1.0000
14.250 1.3409 0.06237 0.05652 -0.0311 0.0079 1.0000
14.500 1.3313 0.06721 0.06153 -0.0327 0.0077 1.0000
14.750 1.3191 0.07275 0.06722 -0.0347 0.0074 1.0000
15.000 1.3056 0.07876 0.07340 -0.0372 0.0073 1.0000
15.250 1.2946 0.08462 0.07942 -0.0398 0.0072 1.0000
15.500 1.2844 0.09058 0.08556 -0.0425 0.0070 1.0000
15.750 1.2713 0.09722 0.09237 -0.0457 0.0070 1.0000
16.000 1.2602 0.10376 0.09908 -0.0490 0.0068 1.0000
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Polar data table (+)
Polar graphs
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