SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.61 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7037-il-1000000-n5.txt Download as CSV file: xf-sd7037-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7037-092-88
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 -0.4063 0.08590 0.08425 -0.0332 1.0000 0.0054
-9.000 -0.4103 0.08165 0.08003 -0.0348 1.0000 0.0054
-8.500 -0.5124 0.02416 0.02119 -0.0843 0.9547 0.0055
-8.250 -0.4972 0.02132 0.01795 -0.0839 0.9472 0.0056
-8.000 -0.4773 0.01956 0.01590 -0.0835 0.9416 0.0057
-7.750 -0.4558 0.01808 0.01418 -0.0830 0.9357 0.0058
-7.500 -0.4329 0.01697 0.01287 -0.0825 0.9307 0.0059
-7.250 -0.4088 0.01599 0.01170 -0.0822 0.9256 0.0059
-7.000 -0.3841 0.01520 0.01076 -0.0819 0.9200 0.0060
-6.500 -0.3361 0.01284 0.00801 -0.0811 0.9089 0.0062
-6.250 -0.3107 0.01211 0.00716 -0.0807 0.9030 0.0063
-6.000 -0.2847 0.01153 0.00648 -0.0805 0.8974 0.0065
-5.750 -0.2582 0.01108 0.00596 -0.0803 0.8908 0.0066
-5.500 -0.2316 0.01070 0.00551 -0.0800 0.8846 0.0069
-5.250 -0.2046 0.01031 0.00507 -0.0798 0.8775 0.0071
-5.000 -0.1779 0.00991 0.00458 -0.0796 0.8703 0.0073
-4.750 -0.1508 0.00951 0.00411 -0.0794 0.8621 0.0075
-4.500 -0.1238 0.00916 0.00368 -0.0792 0.8534 0.0078
-4.250 -0.0966 0.00886 0.00331 -0.0790 0.8430 0.0081
-4.000 -0.0692 0.00861 0.00299 -0.0788 0.8320 0.0084
-3.750 -0.0419 0.00841 0.00271 -0.0786 0.8195 0.0085
-3.500 -0.0147 0.00811 0.00232 -0.0784 0.8055 0.0091
-3.250 0.0126 0.00792 0.00206 -0.0781 0.7898 0.0096
-3.000 0.0399 0.00780 0.00185 -0.0779 0.7727 0.0102
-2.750 0.0672 0.00770 0.00167 -0.0777 0.7549 0.0109
-2.250 0.1220 0.00755 0.00136 -0.0773 0.7182 0.0141
-2.000 0.1493 0.00744 0.00123 -0.0772 0.6991 0.0265
-1.750 0.1765 0.00732 0.00112 -0.0770 0.6802 0.0521
-1.500 0.2036 0.00720 0.00105 -0.0769 0.6615 0.0867
-1.250 0.2309 0.00707 0.00099 -0.0768 0.6430 0.1298
-1.000 0.2581 0.00693 0.00094 -0.0768 0.6245 0.1843
-0.750 0.2853 0.00684 0.00092 -0.0767 0.6058 0.2344
-0.250 0.3393 0.00651 0.00092 -0.0766 0.5686 0.3957
0.000 0.3663 0.00641 0.00093 -0.0765 0.5494 0.4681
0.250 0.3933 0.00635 0.00096 -0.0764 0.5304 0.5280
0.750 0.4470 0.00624 0.00106 -0.0761 0.4936 0.6587
1.000 0.4736 0.00622 0.00112 -0.0758 0.4748 0.7157
1.250 0.4999 0.00623 0.00119 -0.0754 0.4565 0.7663
1.500 0.5257 0.00624 0.00127 -0.0749 0.4391 0.8154
1.750 0.5505 0.00626 0.00135 -0.0742 0.4208 0.8648
2.000 0.5737 0.00626 0.00143 -0.0730 0.4034 0.9176
2.250 0.6066 0.00633 0.00148 -0.0740 0.3843 0.9819
2.500 0.6362 0.00651 0.00156 -0.0744 0.3654 1.0000
3.000 0.6899 0.00687 0.00176 -0.0741 0.3308 1.0000
3.250 0.7167 0.00706 0.00187 -0.0739 0.3140 1.0000
3.500 0.7434 0.00726 0.00199 -0.0737 0.2963 1.0000
3.750 0.7700 0.00746 0.00212 -0.0735 0.2796 1.0000
4.000 0.7965 0.00769 0.00227 -0.0733 0.2622 1.0000
4.250 0.8229 0.00791 0.00242 -0.0731 0.2466 1.0000
4.500 0.8492 0.00815 0.00259 -0.0729 0.2303 1.0000
4.750 0.8756 0.00837 0.00276 -0.0727 0.2171 1.0000
5.250 0.9276 0.00889 0.00314 -0.0722 0.1861 1.0000
5.500 0.9524 0.00928 0.00339 -0.0718 0.1606 1.0000
5.750 0.9776 0.00961 0.00364 -0.0714 0.1419 1.0000
6.000 1.0032 0.00990 0.00388 -0.0711 0.1301 1.0000
6.250 1.0284 0.01021 0.00413 -0.0708 0.1167 1.0000
6.500 1.0528 0.01061 0.00444 -0.0703 0.0989 1.0000
6.750 1.0769 0.01103 0.00477 -0.0698 0.0827 1.0000
7.000 1.1015 0.01139 0.00509 -0.0694 0.0716 1.0000
7.250 1.1257 0.01178 0.00542 -0.0689 0.0607 1.0000
7.500 1.1491 0.01225 0.00582 -0.0683 0.0479 1.0000
7.750 1.1724 0.01272 0.00623 -0.0677 0.0374 1.0000
8.000 1.1952 0.01322 0.00668 -0.0670 0.0277 1.0000
8.250 1.2168 0.01383 0.00722 -0.0662 0.0164 1.0000
8.500 1.2377 0.01450 0.00784 -0.0652 0.0087 1.0000
8.750 1.2604 0.01494 0.00831 -0.0645 0.0074 1.0000
9.000 1.2829 0.01540 0.00880 -0.0638 0.0068 1.0000
9.250 1.3046 0.01591 0.00935 -0.0629 0.0062 1.0000
9.500 1.3262 0.01640 0.00989 -0.0621 0.0059 1.0000
9.750 1.3476 0.01689 0.01043 -0.0612 0.0057 1.0000
10.000 1.3682 0.01741 0.01100 -0.0602 0.0055 1.0000
10.250 1.3883 0.01795 0.01160 -0.0592 0.0053 1.0000
10.500 1.4074 0.01854 0.01225 -0.0580 0.0051 1.0000
10.750 1.4257 0.01915 0.01292 -0.0568 0.0050 1.0000
11.000 1.4428 0.01981 0.01365 -0.0553 0.0048 1.0000
11.250 1.4581 0.02050 0.01440 -0.0536 0.0046 1.0000
11.500 1.4701 0.02123 0.01520 -0.0513 0.0045 1.0000
11.750 1.4804 0.02204 0.01608 -0.0489 0.0044 1.0000
12.000 1.4881 0.02302 0.01715 -0.0462 0.0042 1.0000
12.250 1.4920 0.02429 0.01852 -0.0433 0.0040 1.0000
12.500 1.5019 0.02521 0.01952 -0.0413 0.0040 1.0000
12.750 1.5100 0.02627 0.02067 -0.0393 0.0039 1.0000
13.000 1.5163 0.02752 0.02200 -0.0372 0.0039 1.0000
13.250 1.5229 0.02880 0.02338 -0.0354 0.0039 1.0000
13.500 1.5276 0.03030 0.02497 -0.0336 0.0038 1.0000
13.750 1.5305 0.03202 0.02680 -0.0319 0.0038 1.0000
14.000 1.5343 0.03377 0.02864 -0.0306 0.0037 1.0000
14.250 1.5342 0.03598 0.03097 -0.0294 0.0037 1.0000
14.500 1.5336 0.03841 0.03351 -0.0285 0.0036 1.0000
14.750 1.5322 0.04108 0.03629 -0.0280 0.0036 1.0000
15.000 1.5303 0.04398 0.03931 -0.0278 0.0035 1.0000
15.250 1.5253 0.04747 0.04293 -0.0280 0.0035 1.0000
15.500 1.5189 0.05136 0.04695 -0.0287 0.0035 1.0000
15.750 1.5110 0.05570 0.05142 -0.0298 0.0034 1.0000
16.000 1.5005 0.06070 0.05656 -0.0315 0.0034 1.0000
16.250 1.4903 0.06592 0.06190 -0.0335 0.0034 1.0000
16.500 1.4790 0.07157 0.06769 -0.0360 0.0034 1.0000
16.750 1.4635 0.07820 0.07446 -0.0390 0.0034 1.0000
17.000 1.4467 0.08531 0.08171 -0.0425 0.0033 1.0000
17.250 1.4303 0.09261 0.08915 -0.0462 0.0033 1.0000
17.500 1.4116 0.10053 0.09721 -0.0503 0.0034 1.0000
17.750 1.3931 0.10868 0.10549 -0.0546 0.0033 1.0000
18.000 1.3745 0.11699 0.11394 -0.0591 0.0034 1.0000
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Polar data table (+)
Polar graphs
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