SA7038 (sa7038-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.75 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7038-il-1000000-n5.txt Download as CSV file: xf-sa7038-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3727 0.09108 0.08946 -0.0329 1.0000 0.0052
-9.000 -0.3768 0.08661 0.08501 -0.0343 1.0000 0.0049
-8.750 -0.3760 0.08364 0.08207 -0.0351 1.0000 0.0054
-8.500 -0.3686 0.07863 0.07707 -0.0398 0.9899 0.0053
-8.250 -0.3589 0.07182 0.07027 -0.0478 0.9838 0.0053
-8.000 -0.3479 0.06414 0.06259 -0.0588 0.9727 0.0053
-7.750 -0.3425 0.05268 0.05104 -0.0753 0.9537 0.0053
-7.500 -0.3829 0.02837 0.02586 -0.0862 0.9275 0.0057
-7.250 -0.3743 0.02257 0.01946 -0.0862 0.9183 0.0059
-7.000 -0.3550 0.02010 0.01663 -0.0859 0.9120 0.0060
-6.750 -0.3331 0.01820 0.01442 -0.0856 0.9051 0.0061
-6.500 -0.3099 0.01678 0.01274 -0.0853 0.8988 0.0062
-6.250 -0.2853 0.01563 0.01138 -0.0850 0.8914 0.0063
-6.000 -0.2601 0.01470 0.01025 -0.0847 0.8847 0.0064
-5.750 -0.2339 0.01407 0.00947 -0.0845 0.8776 0.0065
-5.500 -0.2074 0.01364 0.00891 -0.0842 0.8708 0.0066
-5.250 -0.1819 0.01239 0.00746 -0.0840 0.8632 0.0066
-5.000 -0.1559 0.01153 0.00646 -0.0837 0.8553 0.0067
-4.750 -0.1298 0.01067 0.00545 -0.0834 0.8461 0.0067
-4.500 -0.1035 0.00993 0.00458 -0.0831 0.8360 0.0069
-4.250 -0.0768 0.00939 0.00393 -0.0829 0.8254 0.0070
-4.000 -0.0499 0.00897 0.00342 -0.0827 0.8144 0.0073
-3.750 -0.0226 0.00866 0.00303 -0.0825 0.8026 0.0076
-3.500 0.0049 0.00840 0.00270 -0.0824 0.7906 0.0080
-3.250 0.0324 0.00819 0.00241 -0.0822 0.7776 0.0084
-3.000 0.0600 0.00801 0.00215 -0.0821 0.7638 0.0089
-2.750 0.0875 0.00788 0.00192 -0.0819 0.7481 0.0092
-2.500 0.1149 0.00778 0.00173 -0.0817 0.7303 0.0095
-2.250 0.1424 0.00770 0.00155 -0.0816 0.7124 0.0097
-2.000 0.1700 0.00764 0.00142 -0.0815 0.6951 0.0101
-1.750 0.1976 0.00758 0.00126 -0.0813 0.6784 0.0112
-1.500 0.2253 0.00755 0.00115 -0.0812 0.6618 0.0124
-1.250 0.2528 0.00747 0.00105 -0.0811 0.6453 0.0250
-1.000 0.2802 0.00732 0.00098 -0.0810 0.6282 0.0672
-0.750 0.3075 0.00719 0.00094 -0.0810 0.6101 0.1180
-0.500 0.3346 0.00700 0.00091 -0.0810 0.5913 0.1997
-0.250 0.3615 0.00677 0.00091 -0.0810 0.5724 0.3051
0.000 0.3883 0.00650 0.00094 -0.0811 0.5541 0.4324
0.250 0.4153 0.00634 0.00097 -0.0810 0.5361 0.5265
0.500 0.4424 0.00631 0.00101 -0.0809 0.5183 0.5831
0.750 0.4694 0.00627 0.00106 -0.0808 0.5012 0.6423
1.000 0.4962 0.00624 0.00112 -0.0806 0.4843 0.7022
1.250 0.5225 0.00620 0.00120 -0.0802 0.4675 0.7654
1.500 0.5475 0.00615 0.00128 -0.0795 0.4500 0.8357
1.750 0.5694 0.00611 0.00136 -0.0780 0.4326 0.9105
2.000 0.5999 0.00616 0.00141 -0.0785 0.4129 0.9827
2.250 0.6299 0.00632 0.00147 -0.0790 0.3941 1.0000
2.500 0.6568 0.00650 0.00156 -0.0789 0.3767 1.0000
2.750 0.6839 0.00666 0.00165 -0.0787 0.3622 1.0000
3.000 0.7108 0.00683 0.00175 -0.0786 0.3469 1.0000
3.250 0.7375 0.00702 0.00186 -0.0784 0.3295 1.0000
3.500 0.7641 0.00723 0.00198 -0.0782 0.3108 1.0000
3.750 0.7904 0.00747 0.00212 -0.0780 0.2908 1.0000
4.000 0.8169 0.00767 0.00227 -0.0778 0.2758 1.0000
4.250 0.8434 0.00789 0.00242 -0.0776 0.2598 1.0000
4.500 0.8697 0.00811 0.00258 -0.0774 0.2445 1.0000
4.750 0.8961 0.00833 0.00274 -0.0772 0.2318 1.0000
5.000 0.9223 0.00856 0.00293 -0.0770 0.2182 1.0000
5.250 0.9482 0.00882 0.00312 -0.0767 0.2033 1.0000
5.500 0.9741 0.00907 0.00332 -0.0765 0.1907 1.0000
5.750 0.9995 0.00936 0.00355 -0.0762 0.1740 1.0000
6.000 1.0248 0.00967 0.00380 -0.0758 0.1579 1.0000
6.250 1.0499 0.00998 0.00405 -0.0755 0.1440 1.0000
6.500 1.0749 0.01030 0.00432 -0.0751 0.1307 1.0000
6.750 1.0990 0.01071 0.00463 -0.0746 0.1132 1.0000
7.000 1.1224 0.01119 0.00500 -0.0740 0.0917 1.0000
7.250 1.1461 0.01161 0.00535 -0.0735 0.0779 1.0000
7.500 1.1689 0.01212 0.00576 -0.0728 0.0619 1.0000
7.750 1.1925 0.01253 0.00613 -0.0723 0.0518 1.0000
8.000 1.2156 0.01298 0.00653 -0.0717 0.0421 1.0000
8.250 1.2381 0.01346 0.00698 -0.0710 0.0333 1.0000
8.500 1.2604 0.01395 0.00744 -0.0702 0.0258 1.0000
8.750 1.2824 0.01446 0.00792 -0.0694 0.0198 1.0000
9.000 1.3036 0.01501 0.00845 -0.0686 0.0143 1.0000
9.250 1.3240 0.01561 0.00903 -0.0676 0.0090 1.0000
9.500 1.3428 0.01634 0.00974 -0.0663 0.0041 1.0000
9.750 1.3626 0.01695 0.01040 -0.0652 0.0030 1.0000
10.000 1.3827 0.01748 0.01098 -0.0642 0.0027 1.0000
10.250 1.4019 0.01804 0.01160 -0.0630 0.0024 1.0000
10.500 1.4204 0.01862 0.01224 -0.0618 0.0023 1.0000
10.750 1.4375 0.01928 0.01295 -0.0603 0.0021 1.0000
11.000 1.4529 0.01993 0.01367 -0.0585 0.0020 1.0000
11.250 1.4656 0.02061 0.01442 -0.0564 0.0019 1.0000
11.500 1.4756 0.02144 0.01535 -0.0538 0.0018 1.0000
11.750 1.4858 0.02228 0.01628 -0.0515 0.0017 1.0000
12.000 1.4934 0.02332 0.01742 -0.0489 0.0016 1.0000
12.250 1.5019 0.02432 0.01851 -0.0467 0.0016 1.0000
12.500 1.5117 0.02527 0.01953 -0.0447 0.0016 1.0000
12.750 1.5189 0.02644 0.02080 -0.0427 0.0016 1.0000
13.000 1.5257 0.02768 0.02213 -0.0407 0.0016 1.0000
13.250 1.5320 0.02902 0.02356 -0.0389 0.0015 1.0000
13.500 1.5349 0.03070 0.02535 -0.0371 0.0015 1.0000
13.750 1.5389 0.03238 0.02713 -0.0356 0.0015 1.0000
14.000 1.5415 0.03427 0.02912 -0.0342 0.0015 1.0000
14.250 1.5437 0.03630 0.03125 -0.0331 0.0015 1.0000
14.500 1.5412 0.03894 0.03402 -0.0322 0.0014 1.0000
14.750 1.5413 0.04148 0.03668 -0.0317 0.0014 1.0000
15.000 1.5382 0.04453 0.03985 -0.0314 0.0014 1.0000
15.250 1.5330 0.04803 0.04348 -0.0316 0.0014 1.0000
15.500 1.5262 0.05196 0.04755 -0.0322 0.0014 1.0000
15.750 1.5215 0.05585 0.05155 -0.0331 0.0013 1.0000
16.000 1.5084 0.06122 0.05707 -0.0349 0.0013 1.0000
16.250 1.5002 0.06611 0.06209 -0.0367 0.0013 1.0000
16.500 1.4881 0.07188 0.06800 -0.0391 0.0013 1.0000
16.750 1.4702 0.07896 0.07524 -0.0423 0.0013 1.0000
17.000 1.4558 0.08567 0.08209 -0.0456 0.0013 1.0000
17.250 1.4379 0.09332 0.08988 -0.0494 0.0013 1.0000
17.500 1.4178 0.10162 0.09833 -0.0537 0.0013 1.0000
17.750 1.3974 0.11025 0.10710 -0.0583 0.0013 1.0000
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Polar data table (+)
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