SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 100,000 Max Cl/Cd: 55.22 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7037-il-100000.txt Download as CSV file: xf-sd7037-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3686 0.10006 0.09510 -0.0296 1.0000 0.0930
-8.500 -0.3794 0.09810 0.09326 -0.0325 1.0000 0.0956
-8.250 -0.4023 0.09686 0.09218 -0.0353 1.0000 0.0964
-8.000 -0.3760 0.09132 0.08660 -0.0316 1.0000 0.0999
-7.750 -0.3715 0.08876 0.08408 -0.0303 1.0000 0.1033
-7.500 -0.3792 0.08661 0.08203 -0.0297 1.0000 0.1065
-7.250 -0.3982 0.08494 0.08049 -0.0297 1.0000 0.1090
-7.000 -0.4259 0.08260 0.07822 -0.0374 1.0000 0.1108
-6.750 -0.4203 0.07861 0.07433 -0.0330 1.0000 0.1127
-6.500 -0.4133 0.07635 0.07210 -0.0286 1.0000 0.1157
-6.250 -0.4144 0.07385 0.06964 -0.0280 1.0000 0.1194
-6.000 -0.4263 0.06939 0.06505 -0.0365 1.0000 0.1265
-5.750 -0.4192 0.06686 0.06265 -0.0317 1.0000 0.1288
-5.500 -0.4139 0.06448 0.06029 -0.0301 1.0000 0.1338
-5.250 -0.4096 0.06041 0.05609 -0.0337 1.0000 0.1428
-5.000 -0.3997 0.05743 0.05288 -0.0368 1.0000 0.1559
-4.750 -0.3913 0.05461 0.05022 -0.0337 1.0000 0.1587
-4.500 -0.3785 0.05163 0.04710 -0.0351 1.0000 0.1723
-4.250 -0.3277 0.03733 0.03108 -0.0453 1.0000 0.0841
-4.000 -0.2997 0.03241 0.02553 -0.0456 1.0000 0.0669
-3.750 -0.2747 0.02936 0.02209 -0.0458 1.0000 0.0639
-3.500 -0.2493 0.02723 0.01949 -0.0458 1.0000 0.0644
-3.250 -0.2239 0.02543 0.01727 -0.0454 1.0000 0.0652
-3.000 -0.1990 0.02382 0.01531 -0.0449 1.0000 0.0655
-2.750 -0.1746 0.02257 0.01378 -0.0443 1.0000 0.0669
-2.500 -0.1468 0.02145 0.01246 -0.0443 0.9987 0.0699
-2.250 -0.1029 0.02040 0.01144 -0.0475 0.9919 0.0836
-2.000 -0.0590 0.01914 0.01046 -0.0507 0.9853 0.1222
-1.750 -0.0223 0.01694 0.01005 -0.0532 0.9786 0.4425
-1.500 0.0069 0.01593 0.01047 -0.0513 0.9720 0.8662
-1.250 0.0622 0.01597 0.01016 -0.0569 0.9612 1.0000
-1.000 0.1053 0.01625 0.01010 -0.0602 0.9501 1.0000
-0.750 0.1501 0.01649 0.01008 -0.0637 0.9394 1.0000
-0.500 0.1991 0.01667 0.01003 -0.0678 0.9302 1.0000
-0.250 0.2384 0.01676 0.00995 -0.0701 0.9177 1.0000
0.000 0.2790 0.01681 0.00986 -0.0724 0.9057 1.0000
0.250 0.3241 0.01677 0.00970 -0.0755 0.8954 1.0000
0.500 0.3721 0.01660 0.00943 -0.0789 0.8862 1.0000
0.750 0.4085 0.01648 0.00924 -0.0801 0.8732 1.0000
1.000 0.4446 0.01630 0.00901 -0.0810 0.8604 1.0000
1.250 0.4799 0.01608 0.00874 -0.0817 0.8475 1.0000
1.500 0.5142 0.01582 0.00845 -0.0820 0.8344 1.0000
1.750 0.5469 0.01555 0.00816 -0.0820 0.8204 1.0000
2.000 0.5779 0.01531 0.00788 -0.0817 0.8052 1.0000
2.250 0.6077 0.01509 0.00763 -0.0811 0.7890 1.0000
2.500 0.6370 0.01489 0.00741 -0.0804 0.7718 1.0000
2.750 0.6661 0.01473 0.00718 -0.0796 0.7540 1.0000
3.000 0.6930 0.01470 0.00710 -0.0787 0.7338 1.0000
3.250 0.7195 0.01472 0.00709 -0.0777 0.7123 1.0000
3.500 0.7464 0.01477 0.00706 -0.0768 0.6910 1.0000
3.750 0.7716 0.01493 0.00716 -0.0757 0.6674 1.0000
4.000 0.7970 0.01511 0.00727 -0.0747 0.6439 1.0000
4.250 0.8223 0.01533 0.00743 -0.0737 0.6200 1.0000
4.500 0.8464 0.01561 0.00766 -0.0727 0.5946 1.0000
4.750 0.8708 0.01592 0.00789 -0.0716 0.5698 1.0000
5.000 0.8951 0.01625 0.00813 -0.0706 0.5447 1.0000
5.250 0.9183 0.01663 0.00850 -0.0695 0.5182 1.0000
5.500 0.9414 0.01705 0.00885 -0.0684 0.4919 1.0000
5.750 0.9645 0.01751 0.00923 -0.0674 0.4662 1.0000
6.000 0.9872 0.01800 0.00965 -0.0663 0.4403 1.0000
6.250 1.0091 0.01853 0.01016 -0.0651 0.4136 1.0000
6.500 1.0308 0.01910 0.01069 -0.0640 0.3876 1.0000
6.750 1.0525 0.01974 0.01125 -0.0629 0.3630 1.0000
7.000 1.0735 0.02040 0.01188 -0.0617 0.3383 1.0000
7.250 1.0941 0.02112 0.01260 -0.0606 0.3142 1.0000
7.500 1.1147 0.02191 0.01326 -0.0594 0.2920 1.0000
7.750 1.1340 0.02269 0.01410 -0.0581 0.2689 1.0000
8.000 1.1537 0.02358 0.01490 -0.0570 0.2484 1.0000
8.250 1.1719 0.02446 0.01588 -0.0555 0.2273 1.0000
8.500 1.1903 0.02544 0.01682 -0.0542 0.2082 1.0000
8.750 1.2081 0.02655 0.01792 -0.0529 0.1897 1.0000
9.000 1.2245 0.02769 0.01915 -0.0513 0.1716 1.0000
9.250 1.2391 0.02878 0.02028 -0.0496 0.1540 1.0000
9.500 1.2507 0.02985 0.02125 -0.0477 0.1365 1.0000
9.750 1.2582 0.03082 0.02238 -0.0452 0.1191 1.0000
10.000 1.2656 0.03211 0.02374 -0.0428 0.1030 1.0000
10.250 1.2704 0.03365 0.02529 -0.0402 0.0881 1.0000
10.500 1.2730 0.03549 0.02714 -0.0372 0.0755 1.0000
10.750 1.2785 0.03785 0.02956 -0.0347 0.0653 1.0000
11.000 1.2878 0.04047 0.03223 -0.0329 0.0584 1.0000
11.250 1.2943 0.04253 0.03443 -0.0309 0.0533 1.0000
11.500 1.3059 0.04547 0.03739 -0.0297 0.0493 1.0000
11.750 1.3113 0.04823 0.04051 -0.0277 0.0472 1.0000
12.000 1.3151 0.05123 0.04381 -0.0259 0.0455 1.0000
12.250 1.3153 0.05437 0.04722 -0.0241 0.0444 1.0000
12.500 1.3122 0.05770 0.05082 -0.0226 0.0436 1.0000
12.750 1.3058 0.06128 0.05465 -0.0212 0.0429 1.0000
13.000 1.2955 0.06527 0.05891 -0.0203 0.0426 1.0000
13.250 1.2811 0.06974 0.06365 -0.0200 0.0425 1.0000
13.500 1.2617 0.07485 0.06906 -0.0206 0.0427 1.0000
13.750 1.2378 0.08088 0.07539 -0.0223 0.0429 1.0000
14.000 1.2050 0.08863 0.08347 -0.0261 0.0436 1.0000
14.250 1.1631 0.09897 0.09413 -0.0327 0.0449 1.0000
14.500 1.1201 0.11143 0.10682 -0.0414 0.0463 1.0000
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Polar data table (+)
Polar graphs
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