SA7038 (sa7038-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 500,000 Max Cl/Cd: 102.04 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7038-il-500000.txt Download as CSV file: xf-sa7038-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
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 -0.2819 0.08304 0.08099 -0.0373 1.0000 0.0185
-8.750 -0.2874 0.07989 0.07787 -0.0368 1.0000 0.0186
-8.500 -0.2962 0.07720 0.07522 -0.0354 1.0000 0.0186
-8.250 -0.3073 0.07480 0.07286 -0.0336 1.0000 0.0186
-8.000 -0.3165 0.06753 0.06563 -0.0366 0.9983 0.0191
-7.750 -0.3055 0.06344 0.06154 -0.0393 0.9959 0.0196
-7.500 -0.2953 0.05903 0.05713 -0.0432 0.9930 0.0199
-7.250 -0.2852 0.05462 0.05273 -0.0476 0.9885 0.0205
-7.000 -0.2718 0.04845 0.04655 -0.0564 0.9844 0.0211
-6.750 -0.2582 0.04128 0.03933 -0.0670 0.9791 0.0218
-6.500 -0.2394 0.03326 0.03116 -0.0775 0.9749 0.0227
-6.250 -0.2108 0.02617 0.02361 -0.0859 0.9713 0.0256
-6.000 -0.2061 0.01795 0.01490 -0.0894 0.9624 0.0265
-5.750 -0.1843 0.01500 0.01190 -0.0909 0.9582 0.0277
-5.500 -0.1653 0.01333 0.01013 -0.0907 0.9510 0.0292
-5.250 -0.1438 0.01141 0.00797 -0.0907 0.9450 0.0317
-5.000 -0.1174 0.01194 0.00816 -0.0891 0.9378 0.0351
-4.750 -0.1039 0.00751 0.00341 -0.0896 0.9316 0.0381
-4.500 -0.0755 0.01561 0.01021 -0.0925 0.9405 0.0189
-4.250 -0.0509 0.01422 0.00869 -0.0917 0.9338 0.0182
-4.000 -0.0249 0.01282 0.00712 -0.0910 0.9288 0.0180
-3.750 -0.0008 0.01190 0.00610 -0.0899 0.9208 0.0181
-3.500 0.0251 0.01120 0.00529 -0.0892 0.9149 0.0184
-3.250 0.0497 0.01034 0.00435 -0.0884 0.9067 0.0192
-3.000 0.0758 0.00973 0.00367 -0.0877 0.9004 0.0206
-2.750 0.1020 0.00939 0.00329 -0.0872 0.8917 0.0227
-2.500 0.1289 0.00912 0.00296 -0.0867 0.8845 0.0255
-2.250 0.1556 0.00865 0.00249 -0.0862 0.8752 0.0420
-2.000 0.1815 0.00798 0.00223 -0.0859 0.8660 0.1602
-1.750 0.2078 0.00755 0.00207 -0.0857 0.8566 0.2568
-1.500 0.2337 0.00707 0.00197 -0.0854 0.8454 0.3836
-1.250 0.2594 0.00663 0.00191 -0.0850 0.8339 0.5166
-1.000 0.2844 0.00622 0.00189 -0.0843 0.8220 0.6513
-0.750 0.3077 0.00588 0.00189 -0.0830 0.8096 0.7713
-0.500 0.3290 0.00565 0.00186 -0.0810 0.7964 0.8647
-0.250 0.3579 0.00552 0.00179 -0.0805 0.7826 0.9585
0.000 0.4003 0.00550 0.00166 -0.0835 0.7670 1.0000
0.250 0.4263 0.00558 0.00161 -0.0830 0.7500 1.0000
0.500 0.4524 0.00567 0.00158 -0.0825 0.7323 1.0000
0.750 0.4787 0.00578 0.00156 -0.0821 0.7144 1.0000
1.000 0.5051 0.00589 0.00157 -0.0817 0.6956 1.0000
1.250 0.5315 0.00602 0.00158 -0.0813 0.6769 1.0000
1.750 0.5843 0.00630 0.00165 -0.0806 0.6391 1.0000
2.000 0.6106 0.00646 0.00171 -0.0802 0.6194 1.0000
2.250 0.6368 0.00663 0.00178 -0.0798 0.5996 1.0000
2.500 0.6631 0.00680 0.00185 -0.0795 0.5789 1.0000
3.000 0.7155 0.00717 0.00205 -0.0788 0.5380 1.0000
3.250 0.7415 0.00738 0.00217 -0.0785 0.5175 1.0000
3.500 0.7675 0.00758 0.00229 -0.0781 0.4974 1.0000
3.750 0.7935 0.00780 0.00243 -0.0778 0.4770 1.0000
4.000 0.8192 0.00804 0.00260 -0.0774 0.4556 1.0000
4.250 0.8449 0.00828 0.00276 -0.0771 0.4335 1.0000
4.500 0.8703 0.00854 0.00293 -0.0767 0.4119 1.0000
4.750 0.8959 0.00880 0.00312 -0.0763 0.3911 1.0000
5.000 0.9211 0.00909 0.00335 -0.0759 0.3711 1.0000
5.250 0.9464 0.00937 0.00357 -0.0755 0.3499 1.0000
5.500 0.9714 0.00968 0.00381 -0.0751 0.3302 1.0000
5.750 0.9964 0.00999 0.00407 -0.0747 0.3107 1.0000
6.000 1.0210 0.01033 0.00434 -0.0742 0.2901 1.0000
6.250 1.0454 0.01069 0.00464 -0.0737 0.2696 1.0000
6.500 1.0695 0.01108 0.00494 -0.0732 0.2477 1.0000
6.750 1.0933 0.01147 0.00529 -0.0727 0.2289 1.0000
7.000 1.1172 0.01187 0.00563 -0.0722 0.2098 1.0000
7.250 1.1405 0.01231 0.00601 -0.0715 0.1911 1.0000
7.500 1.1635 0.01276 0.00641 -0.0709 0.1736 1.0000
7.750 1.1866 0.01320 0.00681 -0.0703 0.1577 1.0000
8.000 1.2091 0.01369 0.00727 -0.0696 0.1409 1.0000
8.250 1.2307 0.01425 0.00775 -0.0687 0.1231 1.0000
8.500 1.2520 0.01482 0.00825 -0.0679 0.1069 1.0000
8.750 1.2731 0.01538 0.00878 -0.0670 0.0918 1.0000
9.000 1.2934 0.01600 0.00935 -0.0660 0.0777 1.0000
9.250 1.3127 0.01667 0.00997 -0.0649 0.0640 1.0000
9.500 1.3313 0.01739 0.01065 -0.0637 0.0518 1.0000
9.750 1.3495 0.01809 0.01134 -0.0625 0.0430 1.0000
10.000 1.3667 0.01885 0.01210 -0.0611 0.0360 1.0000
10.250 1.3832 0.01961 0.01286 -0.0596 0.0300 1.0000
10.500 1.3987 0.02038 0.01366 -0.0579 0.0239 1.0000
10.750 1.4078 0.02143 0.01469 -0.0553 0.0166 1.0000
11.000 1.4136 0.02267 0.01597 -0.0522 0.0120 1.0000
11.250 1.4153 0.02420 0.01760 -0.0488 0.0099 1.0000
11.500 1.4240 0.02527 0.01879 -0.0465 0.0092 1.0000
11.750 1.4302 0.02654 0.02017 -0.0441 0.0084 1.0000
12.000 1.4353 0.02793 0.02167 -0.0419 0.0080 1.0000
12.250 1.4391 0.02948 0.02332 -0.0397 0.0076 1.0000
12.500 1.4387 0.03145 0.02540 -0.0375 0.0072 1.0000
12.750 1.4323 0.03404 0.02814 -0.0353 0.0069 1.0000
13.000 1.4269 0.03677 0.03102 -0.0337 0.0067 1.0000
13.250 1.4284 0.03902 0.03339 -0.0327 0.0065 1.0000
13.500 1.4264 0.04177 0.03628 -0.0319 0.0063 1.0000
13.750 1.4233 0.04481 0.03946 -0.0315 0.0063 1.0000
14.000 1.4180 0.04833 0.04312 -0.0315 0.0062 1.0000
14.250 1.4117 0.05216 0.04711 -0.0319 0.0061 1.0000
14.500 1.4054 0.05622 0.05132 -0.0327 0.0060 1.0000
14.750 1.3982 0.06063 0.05587 -0.0338 0.0059 1.0000
15.000 1.3891 0.06552 0.06091 -0.0353 0.0059 1.0000
15.250 1.3809 0.07051 0.06604 -0.0372 0.0058 1.0000
15.500 1.3713 0.07592 0.07162 -0.0393 0.0058 1.0000
15.750 1.3612 0.08160 0.07745 -0.0417 0.0058 1.0000
16.000 1.3502 0.08763 0.08363 -0.0444 0.0057 1.0000
16.250 1.3400 0.09370 0.08984 -0.0473 0.0057 1.0000
16.500 1.3285 0.10021 0.09650 -0.0505 0.0056 1.0000
16.750 1.3174 0.10680 0.10322 -0.0539 0.0056 1.0000
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