S8037 (16%) (s8037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: S8037 (16%) (s8037-il) Reynolds number: 1,000,000 Max Cl/Cd: 110.53 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s8037-il-1000000.txt Download as CSV file: xf-s8037-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: S8037 (16%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.7750 0.09005 0.08751 -0.0552 1.0000 0.0081
-16.500 -0.8148 0.07874 0.07599 -0.0618 1.0000 0.0082
-16.250 -0.8369 0.07105 0.06814 -0.0664 1.0000 0.0081
-16.000 -0.8504 0.06523 0.06219 -0.0698 1.0000 0.0080
-15.750 -0.8723 0.05867 0.05549 -0.0733 1.0000 0.0081
-15.500 -0.8828 0.05406 0.05074 -0.0755 1.0000 0.0080
-15.250 -0.8997 0.04907 0.04560 -0.0775 1.0000 0.0081
-15.000 -0.9061 0.04569 0.04217 -0.0786 1.0000 0.0083
-14.750 -0.9203 0.04165 0.03796 -0.0792 1.0000 0.0083
-14.500 -0.9255 0.03881 0.03499 -0.0792 1.0000 0.0082
-14.250 -0.9251 0.03675 0.03288 -0.0789 1.0000 0.0083
-14.000 -0.9284 0.03448 0.03052 -0.0781 1.0000 0.0084
-13.750 -0.9279 0.03273 0.02871 -0.0770 1.0000 0.0085
-13.500 -0.9328 0.03066 0.02651 -0.0752 1.0000 0.0085
-13.250 -0.9304 0.02938 0.02516 -0.0733 1.0000 0.0086
-13.000 -0.9281 0.02824 0.02397 -0.0711 1.0000 0.0088
-12.750 -0.9268 0.02710 0.02275 -0.0685 1.0000 0.0088
-12.500 -0.9261 0.02607 0.02164 -0.0654 1.0000 0.0089
-12.250 -0.9240 0.02494 0.02043 -0.0624 0.9997 0.0089
-12.000 -0.8921 0.02405 0.01946 -0.0648 0.9971 0.0095
-11.750 -0.8635 0.02289 0.01819 -0.0666 0.9927 0.0096
-11.500 -0.8394 0.02182 0.01704 -0.0672 0.9834 0.0098
-11.250 -0.8138 0.02136 0.01649 -0.0674 0.9568 0.0101
-10.750 -0.7096 0.01801 0.01291 -0.0810 0.9319 0.0110
-10.500 -0.6572 0.01716 0.01191 -0.0871 0.9014 0.0114
-10.250 -0.6395 0.01671 0.01124 -0.0856 0.8642 0.0118
-10.000 -0.6275 0.01631 0.01070 -0.0829 0.8405 0.0120
-9.750 -0.6142 0.01596 0.01023 -0.0803 0.8230 0.0123
-9.500 -0.5988 0.01572 0.00987 -0.0780 0.8091 0.0126
-9.250 -0.5890 0.01517 0.00921 -0.0748 0.7967 0.0130
-9.000 -0.5782 0.01457 0.00854 -0.0718 0.7867 0.0133
-8.750 -0.5615 0.01422 0.00811 -0.0698 0.7777 0.0137
-8.500 -0.5428 0.01386 0.00772 -0.0682 0.7696 0.0143
-8.250 -0.5237 0.01356 0.00734 -0.0666 0.7621 0.0147
-8.000 -0.5030 0.01328 0.00701 -0.0652 0.7556 0.0152
-7.750 -0.4823 0.01300 0.00667 -0.0639 0.7490 0.0157
-7.500 -0.4657 0.01251 0.00612 -0.0619 0.7428 0.0166
-7.250 -0.4444 0.01221 0.00580 -0.0606 0.7371 0.0174
-7.000 -0.4226 0.01197 0.00551 -0.0595 0.7313 0.0181
-6.750 -0.4003 0.01175 0.00523 -0.0584 0.7259 0.0188
-6.500 -0.3797 0.01137 0.00483 -0.0570 0.7210 0.0199
-6.250 -0.3577 0.01110 0.00453 -0.0558 0.7157 0.0211
-6.000 -0.3345 0.01094 0.00431 -0.0549 0.7107 0.0225
-5.750 -0.3119 0.01065 0.00402 -0.0538 0.7065 0.0244
-5.500 -0.2884 0.01044 0.00379 -0.0529 0.7017 0.0268
-5.000 -0.2445 0.00988 0.00330 -0.0506 0.6922 0.0473
-4.750 -0.2221 0.00958 0.00311 -0.0495 0.6881 0.0671
-4.500 -0.1990 0.00935 0.00293 -0.0486 0.6835 0.0857
-4.250 -0.1765 0.00911 0.00277 -0.0476 0.6789 0.1098
-4.000 -0.1539 0.00886 0.00261 -0.0465 0.6744 0.1396
-3.750 -0.1319 0.00853 0.00245 -0.0454 0.6700 0.1801
-3.500 -0.1111 0.00818 0.00229 -0.0441 0.6654 0.2362
-3.250 -0.0911 0.00782 0.00214 -0.0426 0.6605 0.3025
-3.000 -0.0707 0.00743 0.00200 -0.0412 0.6563 0.3725
-2.750 -0.0504 0.00706 0.00190 -0.0397 0.6516 0.4452
-2.500 -0.0292 0.00682 0.00182 -0.0383 0.6469 0.5053
-2.250 -0.0065 0.00667 0.00178 -0.0372 0.6421 0.5487
-2.000 0.0179 0.00656 0.00176 -0.0364 0.6375 0.5795
-1.750 0.0432 0.00650 0.00172 -0.0358 0.6327 0.6007
-1.500 0.0683 0.00648 0.00170 -0.0351 0.6277 0.6184
-1.250 0.0940 0.00643 0.00168 -0.0346 0.6233 0.6367
-1.000 0.1195 0.00639 0.00167 -0.0340 0.6182 0.6541
-0.750 0.1449 0.00637 0.00165 -0.0334 0.6133 0.6673
-0.500 0.1704 0.00635 0.00165 -0.0329 0.6084 0.6818
-0.250 0.1959 0.00631 0.00165 -0.0323 0.6029 0.6981
0.000 0.2208 0.00630 0.00164 -0.0316 0.5972 0.7132
0.250 0.2466 0.00630 0.00165 -0.0311 0.5917 0.7258
0.500 0.2723 0.00628 0.00165 -0.0306 0.5861 0.7386
0.750 0.2972 0.00629 0.00166 -0.0299 0.5801 0.7514
1.000 0.3229 0.00628 0.00168 -0.0294 0.5746 0.7641
1.250 0.3483 0.00628 0.00169 -0.0288 0.5682 0.7771
1.500 0.3727 0.00630 0.00171 -0.0281 0.5618 0.7909
1.750 0.3984 0.00627 0.00174 -0.0276 0.5559 0.8053
2.000 0.4230 0.00628 0.00177 -0.0268 0.5494 0.8212
2.250 0.4479 0.00628 0.00182 -0.0262 0.5431 0.8393
2.500 0.4736 0.00626 0.00186 -0.0257 0.5364 0.8592
2.750 0.5002 0.00630 0.00192 -0.0254 0.5294 0.8803
3.000 0.5343 0.00631 0.00201 -0.0268 0.5219 0.9007
3.250 0.5757 0.00642 0.00212 -0.0299 0.5129 0.9177
3.500 0.6218 0.00654 0.00224 -0.0340 0.5024 0.9297
3.750 0.6710 0.00669 0.00237 -0.0389 0.4920 0.9350
4.000 0.7101 0.00688 0.00252 -0.0415 0.4815 0.9430
4.250 0.7474 0.00706 0.00268 -0.0437 0.4709 0.9484
4.500 0.7768 0.00726 0.00285 -0.0440 0.4602 0.9570
4.750 0.8082 0.00748 0.00302 -0.0449 0.4489 0.9627
5.000 0.8336 0.00769 0.00321 -0.0445 0.4376 0.9717
5.250 0.8691 0.00791 0.00339 -0.0464 0.4239 0.9744
5.500 0.9019 0.00816 0.00358 -0.0477 0.4083 0.9785
5.750 0.9295 0.00847 0.00382 -0.0479 0.3907 0.9838
6.000 0.9644 0.00877 0.00402 -0.0498 0.3712 0.9858
6.250 0.9986 0.00906 0.00424 -0.0515 0.3534 0.9884
6.500 1.0309 0.00936 0.00447 -0.0529 0.3353 0.9915
6.750 1.0624 0.00967 0.00472 -0.0541 0.3182 0.9941
7.000 1.0966 0.00997 0.00493 -0.0559 0.2997 0.9960
7.250 1.1297 0.01032 0.00519 -0.0576 0.2801 0.9983
7.500 1.1605 0.01067 0.00546 -0.0588 0.2629 1.0000
7.750 1.1729 0.01093 0.00568 -0.0559 0.2510 1.0000
8.000 1.1842 0.01124 0.00594 -0.0529 0.2387 1.0000
8.250 1.1944 0.01157 0.00622 -0.0497 0.2265 1.0000
8.500 1.2033 0.01192 0.00652 -0.0462 0.2152 1.0000
8.750 1.2109 0.01219 0.00677 -0.0424 0.2059 1.0000
9.000 1.2140 0.01249 0.00704 -0.0378 0.1971 1.0000
9.250 1.2195 0.01282 0.00735 -0.0337 0.1884 1.0000
9.500 1.2276 0.01316 0.00768 -0.0302 0.1806 1.0000
9.750 1.2348 0.01360 0.00809 -0.0267 0.1721 1.0000
10.000 1.2448 0.01400 0.00848 -0.0238 0.1648 1.0000
10.250 1.2518 0.01455 0.00900 -0.0206 0.1562 1.0000
10.500 1.2626 0.01501 0.00947 -0.0181 0.1500 1.0000
11.000 1.2812 0.01621 0.01066 -0.0130 0.1371 1.0000
11.250 1.2889 0.01697 0.01140 -0.0105 0.1302 1.0000
11.500 1.2998 0.01764 0.01209 -0.0086 0.1248 1.0000
11.750 1.3083 0.01850 0.01294 -0.0065 0.1185 1.0000
12.000 1.3178 0.01935 0.01380 -0.0047 0.1128 1.0000
12.250 1.3270 0.02027 0.01473 -0.0029 0.1074 1.0000
12.500 1.3350 0.02132 0.01578 -0.0012 0.1019 1.0000
12.750 1.3447 0.02231 0.01678 0.0002 0.0971 1.0000
13.000 1.3508 0.02357 0.01803 0.0019 0.0913 1.0000
13.250 1.3606 0.02464 0.01913 0.0031 0.0876 1.0000
13.500 1.3678 0.02590 0.02040 0.0045 0.0835 1.0000
13.750 1.3731 0.02733 0.02185 0.0059 0.0791 1.0000
14.000 1.3825 0.02851 0.02307 0.0069 0.0764 1.0000
14.250 1.3877 0.03002 0.02457 0.0081 0.0723 1.0000
14.500 1.3916 0.03167 0.02625 0.0094 0.0683 1.0000
14.750 1.3993 0.03305 0.02768 0.0102 0.0657 1.0000
15.000 1.4036 0.03475 0.02939 0.0112 0.0626 1.0000
15.250 1.4062 0.03663 0.03129 0.0122 0.0586 1.0000
15.500 1.4127 0.03824 0.03295 0.0129 0.0568 1.0000
15.750 1.4141 0.04033 0.03503 0.0136 0.0525 1.0000
16.000 1.4160 0.04244 0.03718 0.0143 0.0504 1.0000
16.250 1.4221 0.04419 0.03898 0.0148 0.0483 1.0000
16.500 1.4241 0.04638 0.04121 0.0152 0.0461 1.0000
16.750 1.4258 0.04866 0.04354 0.0156 0.0450 1.0000
17.000 1.4250 0.05123 0.04615 0.0160 0.0427 1.0000
17.250 1.4290 0.05335 0.04833 0.0161 0.0416 1.0000
17.500 1.4297 0.05584 0.05087 0.0163 0.0398 1.0000
17.750 1.4296 0.05848 0.05356 0.0163 0.0387 1.0000
18.000 1.4272 0.06142 0.05654 0.0163 0.0371 1.0000
18.250 1.4255 0.06433 0.05952 0.0161 0.0358 1.0000
18.500 1.4262 0.06701 0.06227 0.0159 0.0347 1.0000
18.750 1.4247 0.06999 0.06534 0.0156 0.0344 1.0000
19.000 1.4225 0.07309 0.06850 0.0152 0.0333 1.0000
19.250 1.4168 0.07666 0.07211 0.0146 0.0318 1.0000
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Polar data table (+)
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