SA7036 (sa7036-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7036 (sa7036-il) Reynolds number: 50,000 Max Cl/Cd: 33.61 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7036-il-50000.txt Download as CSV file: xf-sa7036-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: SA7036
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3999 0.11269 0.10589 -0.0199 1.0000 0.2055
-8.750 -0.3805 0.10745 0.10065 -0.0187 1.0000 0.2139
-8.500 -0.4021 0.10757 0.10094 -0.0209 1.0000 0.2203
-8.250 -0.3796 0.10219 0.09555 -0.0192 1.0000 0.2322
-8.000 -0.3731 0.09867 0.09209 -0.0188 1.0000 0.2405
-7.750 -0.3965 0.09866 0.09228 -0.0197 1.0000 0.2490
-7.500 -0.3794 0.09425 0.08788 -0.0181 1.0000 0.2618
-7.250 -0.3715 0.09072 0.08441 -0.0168 1.0000 0.2737
-6.500 -0.3793 0.08350 0.07750 -0.0116 1.0000 0.3112
-6.250 -0.3792 0.08114 0.07524 -0.0090 1.0000 0.3289
-6.000 -0.3878 0.07934 0.07358 -0.0066 1.0000 0.3474
-5.750 -0.4052 0.07817 0.07255 -0.0047 1.0000 0.3643
-5.500 -0.3865 0.07439 0.06880 -0.0005 1.0000 0.3887
-4.750 -0.3795 0.05069 0.04394 -0.0408 1.0000 0.1498
-4.500 -0.3591 0.04571 0.03856 -0.0419 1.0000 0.1324
-4.250 -0.3350 0.04104 0.03303 -0.0436 1.0000 0.1202
-4.000 -0.3141 0.03759 0.02931 -0.0433 1.0000 0.1173
-3.750 -0.2900 0.03438 0.02559 -0.0433 1.0000 0.1138
-3.500 -0.2645 0.03164 0.02231 -0.0431 1.0000 0.1127
-3.250 -0.2393 0.02956 0.01977 -0.0426 1.0000 0.1170
-3.000 -0.2149 0.02774 0.01768 -0.0420 1.0000 0.1254
-2.750 -0.1889 0.02619 0.01573 -0.0411 1.0000 0.1346
-2.500 -0.1651 0.02467 0.01432 -0.0402 1.0000 0.1541
-2.250 -0.1408 0.02319 0.01297 -0.0392 1.0000 0.2012
-2.000 -0.1172 0.01972 0.01180 -0.0376 1.0000 0.5280
-1.750 -0.1007 0.01820 0.01125 -0.0322 1.0000 1.0000
-1.500 -0.0785 0.01842 0.01086 -0.0322 1.0000 1.0000
-1.250 -0.0575 0.01871 0.01069 -0.0321 1.0000 1.0000
-1.000 -0.0371 0.01905 0.01063 -0.0318 1.0000 1.0000
-0.750 -0.0171 0.01944 0.01069 -0.0316 1.0000 1.0000
-0.500 0.0025 0.01989 0.01086 -0.0314 1.0000 1.0000
-0.250 0.0216 0.02039 0.01112 -0.0312 1.0000 1.0000
0.000 0.0404 0.02095 0.01144 -0.0311 1.0000 1.0000
0.250 0.0587 0.02157 0.01187 -0.0310 1.0000 1.0000
0.500 0.0766 0.02225 0.01239 -0.0310 1.0000 1.0000
0.750 0.1158 0.02337 0.01332 -0.0349 0.9898 1.0000
1.000 0.1712 0.02474 0.01448 -0.0416 0.9719 1.0000
1.250 0.2206 0.02586 0.01547 -0.0469 0.9527 1.0000
1.500 0.2682 0.02684 0.01635 -0.0516 0.9332 1.0000
1.750 0.3199 0.02776 0.01721 -0.0567 0.9147 1.0000
2.000 0.3578 0.02845 0.01788 -0.0593 0.8940 1.0000
2.250 0.4036 0.02906 0.01849 -0.0628 0.8745 1.0000
2.500 0.4475 0.02955 0.01901 -0.0657 0.8551 1.0000
2.750 0.4861 0.02996 0.01946 -0.0676 0.8344 1.0000
3.000 0.5371 0.03003 0.01963 -0.0709 0.8161 1.0000
3.250 0.5724 0.03027 0.01995 -0.0717 0.7950 1.0000
3.500 0.6169 0.03009 0.01987 -0.0732 0.7760 1.0000
3.750 0.6650 0.02951 0.01946 -0.0746 0.7584 1.0000
4.000 0.6920 0.02969 0.01973 -0.0736 0.7357 1.0000
4.250 0.7353 0.02899 0.01915 -0.0738 0.7170 1.0000
4.500 0.7635 0.02901 0.01932 -0.0725 0.6940 1.0000
4.750 0.8034 0.02826 0.01866 -0.0719 0.6736 1.0000
5.000 0.8293 0.02837 0.01887 -0.0702 0.6489 1.0000
5.500 0.8896 0.02808 0.01873 -0.0672 0.6005 1.0000
5.750 0.9164 0.02823 0.01892 -0.0656 0.5746 1.0000
6.000 0.9405 0.02862 0.01937 -0.0639 0.5478 1.0000
6.250 0.9646 0.02905 0.01988 -0.0621 0.5206 1.0000
6.500 0.9884 0.02953 0.02040 -0.0604 0.4930 1.0000
6.750 1.0116 0.03010 0.02099 -0.0587 0.4651 1.0000
7.000 1.0341 0.03077 0.02168 -0.0569 0.4372 1.0000
7.250 1.0560 0.03153 0.02245 -0.0552 0.4091 1.0000
7.500 1.0772 0.03243 0.02343 -0.0535 0.3814 1.0000
7.750 1.0976 0.03342 0.02443 -0.0517 0.3536 1.0000
8.000 1.1171 0.03448 0.02549 -0.0499 0.3258 1.0000
8.250 1.1360 0.03568 0.02669 -0.0481 0.2985 1.0000
8.500 1.1540 0.03697 0.02797 -0.0462 0.2715 1.0000
8.750 1.1717 0.03837 0.02935 -0.0444 0.2452 1.0000
9.000 1.1873 0.04015 0.03119 -0.0425 0.2212 1.0000
9.250 1.1987 0.04222 0.03343 -0.0403 0.1994 1.0000
9.500 1.2147 0.04443 0.03565 -0.0386 0.1800 1.0000
9.750 1.2274 0.04683 0.03810 -0.0368 0.1627 1.0000
10.000 1.2388 0.04987 0.04132 -0.0350 0.1496 1.0000
10.250 1.2504 0.05279 0.04433 -0.0333 0.1370 1.0000
10.500 1.2375 0.05674 0.04900 -0.0299 0.1321 1.0000
10.750 1.2508 0.06026 0.05250 -0.0287 0.1231 1.0000
11.000 1.2326 0.06474 0.05752 -0.0258 0.1216 1.0000
11.250 1.2109 0.06927 0.06242 -0.0233 0.1209 1.0000
11.500 1.1863 0.07376 0.06715 -0.0212 0.1211 1.0000
11.750 1.1602 0.07886 0.07243 -0.0204 0.1218 1.0000
12.000 1.1348 0.08470 0.07841 -0.0211 0.1226 1.0000
12.250 1.1108 0.09133 0.08513 -0.0230 0.1234 1.0000
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Polar data table (+)
Polar graphs
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