SA7038 (sa7038-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 100,000 Max Cl/Cd: 56.2 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7038-il-100000.txt Download as CSV file: xf-sa7038-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3531 0.10442 0.09947 -0.0308 1.0000 0.0835
-8.750 -0.3671 0.10310 0.09828 -0.0345 1.0000 0.0858
-8.500 -0.3812 0.10161 0.09691 -0.0369 1.0000 0.0862
-8.250 -0.3533 0.09552 0.09078 -0.0325 1.0000 0.0900
-8.000 -0.3500 0.09291 0.08822 -0.0317 1.0000 0.0929
-7.750 -0.3545 0.09063 0.08603 -0.0315 1.0000 0.0960
-7.500 -0.3704 0.08914 0.08468 -0.0312 1.0000 0.0984
-7.250 -0.3964 0.08800 0.08369 -0.0328 1.0000 0.0997
-7.000 -0.4180 0.08577 0.08148 -0.0388 1.0000 0.1003
-6.750 -0.4015 0.08165 0.07747 -0.0295 1.0000 0.1029
-6.500 -0.3996 0.07940 0.07527 -0.0267 1.0000 0.1058
-6.250 -0.4042 0.07695 0.07287 -0.0266 1.0000 0.1093
-6.000 -0.4188 0.07297 0.06874 -0.0376 1.0000 0.1149
-5.750 -0.4126 0.07008 0.06601 -0.0315 1.0000 0.1168
-5.500 -0.4084 0.06784 0.06382 -0.0286 1.0000 0.1208
-5.250 -0.4043 0.06349 0.05929 -0.0351 1.0000 0.1300
-5.000 -0.3982 0.06118 0.05708 -0.0315 1.0000 0.1332
-4.750 -0.3875 0.05749 0.05322 -0.0351 1.0000 0.1449
-4.500 -0.3786 0.05527 0.05105 -0.0328 1.0000 0.1497
-4.250 -0.3651 0.05207 0.04775 -0.0344 1.0000 0.1617
-4.000 -0.3502 0.04929 0.04487 -0.0353 1.0000 0.1755
-3.750 -0.2832 0.03456 0.02818 -0.0469 1.0000 0.0752
-3.500 -0.2554 0.03101 0.02415 -0.0473 1.0000 0.0652
-3.250 -0.2276 0.02825 0.02074 -0.0476 1.0000 0.0629
-3.000 -0.1988 0.02636 0.01843 -0.0480 0.9990 0.0633
-2.750 -0.1535 0.02430 0.01584 -0.0509 0.9935 0.0626
-2.500 -0.1106 0.02283 0.01412 -0.0536 0.9868 0.0643
-2.250 -0.0678 0.02171 0.01286 -0.0561 0.9799 0.0695
-2.000 -0.0246 0.02074 0.01192 -0.0590 0.9725 0.0850
-1.500 0.0415 0.01675 0.01111 -0.0603 0.9589 0.7589
-1.250 0.0915 0.01649 0.01079 -0.0640 0.9492 1.0000
-1.000 0.1368 0.01675 0.01068 -0.0675 0.9397 1.0000
-0.750 0.1821 0.01693 0.01056 -0.0710 0.9300 1.0000
-0.500 0.2207 0.01707 0.01047 -0.0731 0.9184 1.0000
-0.250 0.2611 0.01716 0.01038 -0.0755 0.9074 1.0000
0.000 0.3135 0.01710 0.01013 -0.0800 0.9003 1.0000
0.250 0.3513 0.01707 0.00998 -0.0816 0.8881 1.0000
0.500 0.3888 0.01699 0.00980 -0.0831 0.8762 1.0000
0.750 0.4267 0.01685 0.00957 -0.0845 0.8649 1.0000
1.000 0.4669 0.01658 0.00923 -0.0861 0.8550 1.0000
1.250 0.5039 0.01630 0.00890 -0.0869 0.8440 1.0000
1.500 0.5354 0.01610 0.00865 -0.0869 0.8306 1.0000
1.750 0.5666 0.01588 0.00839 -0.0866 0.8169 1.0000
2.000 0.5971 0.01566 0.00814 -0.0862 0.8027 1.0000
2.250 0.6272 0.01543 0.00787 -0.0857 0.7879 1.0000
2.500 0.6567 0.01523 0.00762 -0.0851 0.7725 1.0000
2.750 0.6827 0.01519 0.00755 -0.0840 0.7538 1.0000
3.000 0.7099 0.01512 0.00747 -0.0831 0.7352 1.0000
3.250 0.7378 0.01506 0.00734 -0.0823 0.7169 1.0000
3.500 0.7637 0.01513 0.00736 -0.0813 0.6962 1.0000
3.750 0.7900 0.01521 0.00738 -0.0804 0.6753 1.0000
4.000 0.8154 0.01537 0.00751 -0.0794 0.6532 1.0000
4.250 0.8411 0.01555 0.00761 -0.0785 0.6311 1.0000
4.500 0.8654 0.01580 0.00782 -0.0774 0.6072 1.0000
4.750 0.8904 0.01606 0.00800 -0.0765 0.5843 1.0000
5.000 0.9146 0.01637 0.00829 -0.0755 0.5601 1.0000
5.250 0.9381 0.01673 0.00861 -0.0744 0.5355 1.0000
5.500 0.9618 0.01712 0.00892 -0.0734 0.5113 1.0000
5.750 0.9852 0.01753 0.00926 -0.0723 0.4870 1.0000
6.000 1.0076 0.01799 0.00973 -0.0712 0.4614 1.0000
6.250 1.0298 0.01848 0.01019 -0.0701 0.4364 1.0000
6.500 1.0521 0.01902 0.01065 -0.0690 0.4124 1.0000
6.750 1.0736 0.01959 0.01119 -0.0679 0.3879 1.0000
7.000 1.0947 0.02022 0.01185 -0.0667 0.3637 1.0000
7.250 1.1157 0.02090 0.01246 -0.0655 0.3405 1.0000
7.500 1.1359 0.02161 0.01315 -0.0643 0.3173 1.0000
7.750 1.1553 0.02236 0.01391 -0.0630 0.2942 1.0000
8.000 1.1746 0.02318 0.01463 -0.0617 0.2726 1.0000
8.250 1.1920 0.02399 0.01555 -0.0602 0.2498 1.0000
8.500 1.2099 0.02492 0.01638 -0.0588 0.2295 1.0000
8.750 1.2260 0.02587 0.01743 -0.0572 0.2086 1.0000
9.000 1.2420 0.02694 0.01843 -0.0556 0.1896 1.0000
9.250 1.2562 0.02809 0.01965 -0.0538 0.1707 1.0000
9.500 1.2698 0.02935 0.02095 -0.0519 0.1529 1.0000
9.750 1.2824 0.03069 0.02225 -0.0501 0.1366 1.0000
10.000 1.2957 0.03230 0.02386 -0.0483 0.1220 1.0000
10.250 1.3075 0.03393 0.02554 -0.0464 0.1091 1.0000
10.500 1.3178 0.03563 0.02739 -0.0443 0.0979 1.0000
10.750 1.3284 0.03766 0.02958 -0.0423 0.0880 1.0000
11.000 1.3352 0.03956 0.03153 -0.0401 0.0791 1.0000
11.250 1.3413 0.04154 0.03337 -0.0381 0.0700 1.0000
11.500 1.3350 0.04312 0.03537 -0.0344 0.0642 1.0000
11.750 1.3382 0.04557 0.03777 -0.0325 0.0574 1.0000
12.000 1.3330 0.04792 0.04048 -0.0298 0.0526 1.0000
12.250 1.3376 0.05101 0.04344 -0.0286 0.0471 1.0000
12.500 1.3290 0.05396 0.04682 -0.0264 0.0448 1.0000
12.750 1.3235 0.05749 0.05072 -0.0249 0.0427 1.0000
13.000 1.3162 0.06119 0.05469 -0.0239 0.0411 1.0000
13.250 1.3083 0.06502 0.05873 -0.0233 0.0398 1.0000
13.500 1.3009 0.06916 0.06303 -0.0231 0.0387 1.0000
13.750 1.2897 0.07395 0.06803 -0.0235 0.0382 1.0000
14.000 1.2744 0.07939 0.07369 -0.0245 0.0378 1.0000
14.250 1.2551 0.08530 0.07986 -0.0264 0.0377 1.0000
14.500 1.2316 0.09192 0.08677 -0.0297 0.0380 1.0000
14.750 1.1902 0.10239 0.09764 -0.0366 0.0398 1.0000
15.000 1.1365 0.11770 0.11330 -0.0476 0.0432 1.0000
15.250 1.1042 0.13024 0.12595 -0.0560 0.0453 1.0000
15.500 1.0812 0.14144 0.13717 -0.0628 0.0467 1.0000
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Polar data table (+)
Polar graphs
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