SD7032-099-88 (sd7032-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7032-099-88 (sd7032-il) Reynolds number: 100,000 Max Cl/Cd: 56.3 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7032-il-100000.txt Download as CSV file: xf-sd7032-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: SD7032-099-88
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3225 0.10437 0.09952 -0.0353 1.0000 0.0817
-8.750 -0.3161 0.10156 0.09675 -0.0345 1.0000 0.0842
-8.500 -0.3159 0.09904 0.09429 -0.0344 1.0000 0.0873
-8.250 -0.3219 0.09701 0.09236 -0.0349 1.0000 0.0901
-8.000 -0.3423 0.09618 0.09167 -0.0355 1.0000 0.0918
-7.750 -0.3671 0.09568 0.09133 -0.0341 1.0000 0.0922
-7.500 -0.3902 0.09447 0.09024 -0.0351 1.0000 0.0926
-7.250 -0.3727 0.08950 0.08530 -0.0291 1.0000 0.0949
-7.000 -0.3716 0.08735 0.08318 -0.0261 1.0000 0.0971
-6.750 -0.3794 0.08555 0.08145 -0.0241 1.0000 0.0992
-6.500 -0.3900 0.08352 0.07950 -0.0234 1.0000 0.1020
-6.250 -0.4036 0.08105 0.07709 -0.0268 1.0000 0.1053
-6.000 -0.4145 0.07672 0.07273 -0.0348 1.0000 0.1077
-5.750 -0.4106 0.07444 0.07055 -0.0285 1.0000 0.1097
-5.500 -0.4081 0.07229 0.06844 -0.0260 1.0000 0.1130
-5.250 -0.4025 0.06738 0.06328 -0.0367 1.0000 0.1223
-5.000 -0.3987 0.06505 0.06111 -0.0319 1.0000 0.1246
-4.750 -0.3860 0.06134 0.05720 -0.0371 1.0000 0.1373
-4.500 -0.3734 0.05928 0.05530 -0.0340 0.9981 0.1430
-4.250 -0.3303 0.05430 0.05003 -0.0440 0.9910 0.1676
-4.000 -0.2941 0.05071 0.04640 -0.0481 0.9846 0.1843
-3.750 -0.2115 0.03482 0.02836 -0.0637 0.9832 0.0761
-3.500 -0.1683 0.03018 0.02284 -0.0668 0.9776 0.0680
-3.250 -0.1234 0.02812 0.02040 -0.0704 0.9718 0.0718
-3.000 -0.0832 0.02605 0.01783 -0.0724 0.9645 0.0725
-2.750 -0.0372 0.02477 0.01609 -0.0753 0.9582 0.0784
-2.500 -0.0009 0.02327 0.01461 -0.0769 0.9499 0.0856
-2.250 0.0444 0.02218 0.01353 -0.0800 0.9435 0.1007
-2.000 0.0791 0.02116 0.01265 -0.0811 0.9338 0.1264
-1.750 0.1206 0.01870 0.01207 -0.0841 0.9288 0.4970
-1.500 0.1386 0.01802 0.01231 -0.0805 0.9179 0.7739
-1.250 0.1872 0.01758 0.01192 -0.0830 0.9103 1.0000
-1.000 0.2312 0.01760 0.01161 -0.0861 0.9009 1.0000
-0.750 0.2689 0.01764 0.01139 -0.0880 0.8898 1.0000
-0.500 0.3221 0.01747 0.01096 -0.0923 0.8841 1.0000
-0.250 0.3553 0.01745 0.01077 -0.0931 0.8720 1.0000
0.000 0.3898 0.01739 0.01055 -0.0941 0.8606 1.0000
0.250 0.4282 0.01720 0.01023 -0.0954 0.8512 1.0000
0.500 0.4659 0.01695 0.00985 -0.0965 0.8416 1.0000
0.750 0.4964 0.01683 0.00964 -0.0965 0.8290 1.0000
1.000 0.5275 0.01668 0.00940 -0.0964 0.8167 1.0000
1.250 0.5590 0.01649 0.00913 -0.0963 0.8047 1.0000
1.500 0.5908 0.01627 0.00883 -0.0962 0.7930 1.0000
1.750 0.6229 0.01601 0.00849 -0.0961 0.7813 1.0000
2.000 0.6521 0.01586 0.00827 -0.0955 0.7675 1.0000
2.250 0.6804 0.01577 0.00811 -0.0949 0.7529 1.0000
2.500 0.7077 0.01575 0.00802 -0.0942 0.7370 1.0000
2.750 0.7344 0.01577 0.00801 -0.0934 0.7202 1.0000
3.000 0.7613 0.01581 0.00799 -0.0927 0.7030 1.0000
3.250 0.7883 0.01587 0.00797 -0.0920 0.6856 1.0000
3.500 0.8155 0.01595 0.00797 -0.0913 0.6681 1.0000
3.750 0.8429 0.01605 0.00800 -0.0907 0.6507 1.0000
4.000 0.8678 0.01629 0.00820 -0.0898 0.6308 1.0000
4.250 0.8935 0.01651 0.00835 -0.0891 0.6116 1.0000
4.500 0.9197 0.01674 0.00852 -0.0884 0.5932 1.0000
4.750 0.9447 0.01705 0.00879 -0.0876 0.5737 1.0000
5.000 0.9694 0.01738 0.00909 -0.0868 0.5542 1.0000
5.250 0.9946 0.01772 0.00936 -0.0861 0.5354 1.0000
5.500 1.0196 0.01811 0.00971 -0.0854 0.5170 1.0000
5.750 1.0431 0.01854 0.01016 -0.0845 0.4972 1.0000
6.000 1.0674 0.01897 0.01056 -0.0838 0.4785 1.0000
6.250 1.0918 0.01944 0.01095 -0.0830 0.4605 1.0000
6.500 1.1148 0.01995 0.01150 -0.0822 0.4415 1.0000
6.750 1.1375 0.02047 0.01204 -0.0812 0.4225 1.0000
7.000 1.1605 0.02100 0.01254 -0.0804 0.4042 1.0000
7.250 1.1836 0.02157 0.01306 -0.0795 0.3863 1.0000
7.500 1.2043 0.02217 0.01375 -0.0784 0.3672 1.0000
7.750 1.2253 0.02278 0.01439 -0.0773 0.3486 1.0000
8.000 1.2463 0.02341 0.01499 -0.0762 0.3307 1.0000
8.250 1.2669 0.02410 0.01563 -0.0751 0.3132 1.0000
8.500 1.2849 0.02479 0.01647 -0.0737 0.2947 1.0000
8.750 1.3028 0.02552 0.01725 -0.0723 0.2768 1.0000
9.000 1.3202 0.02627 0.01801 -0.0708 0.2593 1.0000
9.250 1.3371 0.02712 0.01881 -0.0693 0.2422 1.0000
9.500 1.3508 0.02804 0.01983 -0.0674 0.2244 1.0000
9.750 1.3636 0.02904 0.02093 -0.0654 0.2067 1.0000
10.000 1.3749 0.03011 0.02200 -0.0633 0.1895 1.0000
10.250 1.3853 0.03133 0.02318 -0.0612 0.1733 1.0000
10.500 1.3957 0.03277 0.02454 -0.0591 0.1580 1.0000
10.750 1.4035 0.03425 0.02602 -0.0568 0.1441 1.0000
11.000 1.4080 0.03567 0.02755 -0.0540 0.1324 1.0000
11.250 1.4128 0.03733 0.02935 -0.0513 0.1218 1.0000
11.500 1.4184 0.03914 0.03127 -0.0491 0.1125 1.0000
11.750 1.4282 0.04106 0.03310 -0.0475 0.1037 1.0000
12.000 1.4284 0.04294 0.03525 -0.0449 0.0968 1.0000
12.250 1.4355 0.04518 0.03751 -0.0433 0.0898 1.0000
12.500 1.4358 0.04735 0.03987 -0.0413 0.0840 1.0000
12.750 1.4422 0.04994 0.04250 -0.0399 0.0780 1.0000
13.000 1.4370 0.05263 0.04549 -0.0380 0.0737 1.0000
13.250 1.4474 0.05544 0.04817 -0.0372 0.0676 1.0000
13.500 1.4346 0.05868 0.05181 -0.0355 0.0651 1.0000
13.750 1.4250 0.06212 0.05553 -0.0345 0.0621 1.0000
14.000 1.4354 0.06532 0.05854 -0.0341 0.0567 1.0000
14.250 1.4171 0.06949 0.06309 -0.0337 0.0556 1.0000
14.500 1.3990 0.07427 0.06822 -0.0340 0.0545 1.0000
14.750 1.3807 0.07958 0.07385 -0.0350 0.0533 1.0000
15.000 1.3614 0.08541 0.07996 -0.0367 0.0525 1.0000
15.250 1.3402 0.09190 0.08671 -0.0392 0.0520 1.0000
15.500 1.3150 0.09952 0.09461 -0.0429 0.0522 1.0000
15.750 1.2859 0.10849 0.10385 -0.0479 0.0531 1.0000
16.000 1.2559 0.11850 0.11408 -0.0540 0.0543 1.0000
16.250 1.2271 0.12909 0.12482 -0.0607 0.0556 1.0000
16.500 1.2004 0.14014 0.13596 -0.0676 0.0566 1.0000
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Polar data table (+)
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