EPPLER 655 AIRFOIL (e655-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 655 AIRFOIL (e655-il) Reynolds number: 200,000 Max Cl/Cd: 69.23 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e655-il-200000.txt Download as CSV file: xf-e655-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 655 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.1179 0.09296 0.08887 -0.1154 0.8573 0.0657
-11.250 -0.1192 0.08850 0.08442 -0.1171 0.8519 0.0635
-10.500 -0.4492 0.03810 0.03188 -0.1277 0.8313 0.0254
-10.250 -0.4472 0.03554 0.02906 -0.1259 0.8276 0.0257
-10.000 -0.4370 0.03376 0.02717 -0.1247 0.8239 0.0262
-9.750 -0.4246 0.03240 0.02571 -0.1235 0.8196 0.0268
-9.500 -0.4112 0.03128 0.02445 -0.1222 0.8157 0.0279
-9.250 -0.3999 0.03004 0.02285 -0.1205 0.8124 0.0295
-9.000 -0.3838 0.02840 0.02094 -0.1194 0.8099 0.0308
-8.750 -0.3645 0.02751 0.02006 -0.1188 0.8069 0.0325
-8.500 -0.3450 0.02640 0.01880 -0.1180 0.8038 0.0341
-8.250 -0.3245 0.02513 0.01735 -0.1171 0.8007 0.0363
-8.000 -0.3038 0.02444 0.01670 -0.1165 0.7978 0.0394
-7.750 -0.2824 0.02351 0.01564 -0.1157 0.7952 0.0433
-7.500 -0.2605 0.02284 0.01495 -0.1151 0.7930 0.0474
-7.250 -0.2412 0.02213 0.01426 -0.1142 0.7904 0.0522
-7.000 -0.2208 0.02180 0.01386 -0.1133 0.7875 0.0581
-6.750 -0.2023 0.02113 0.01329 -0.1123 0.7847 0.0653
-6.500 -0.1828 0.02054 0.01273 -0.1114 0.7819 0.0739
-6.250 -0.1624 0.01999 0.01220 -0.1105 0.7794 0.0852
-6.000 -0.1412 0.01949 0.01173 -0.1098 0.7773 0.1002
-5.750 -0.1197 0.01906 0.01133 -0.1091 0.7755 0.1209
-5.500 -0.1027 0.01870 0.01116 -0.1080 0.7726 0.1472
-5.250 -0.0841 0.01836 0.01101 -0.1071 0.7695 0.1830
-5.000 -0.0640 0.01795 0.01082 -0.1065 0.7666 0.2310
-4.750 -0.0428 0.01749 0.01062 -0.1060 0.7641 0.2914
-4.500 -0.0205 0.01705 0.01047 -0.1057 0.7621 0.3647
-4.250 0.0025 0.01661 0.01038 -0.1053 0.7603 0.4503
-4.000 0.0260 0.01640 0.01054 -0.1046 0.7586 0.5421
-3.750 0.0428 0.01679 0.01119 -0.1027 0.7548 0.6056
-3.500 0.0640 0.01724 0.01171 -0.1014 0.7516 0.6473
-3.250 0.0875 0.01769 0.01213 -0.1004 0.7490 0.6758
-3.000 0.1130 0.01807 0.01245 -0.0996 0.7468 0.6985
-2.750 0.1395 0.01842 0.01273 -0.0988 0.7448 0.7163
-2.500 0.1655 0.01879 0.01305 -0.0978 0.7430 0.7304
-2.250 0.1885 0.01929 0.01350 -0.0966 0.7410 0.7430
-2.000 0.1983 0.02014 0.01438 -0.0941 0.7357 0.7557
-1.750 0.2162 0.02065 0.01491 -0.0918 0.7323 0.7649
-1.500 0.2396 0.02096 0.01516 -0.0907 0.7299 0.7756
-1.250 0.2656 0.02117 0.01531 -0.0899 0.7281 0.7862
-1.000 0.2913 0.02133 0.01542 -0.0888 0.7265 0.7943
-0.750 0.3052 0.02199 0.01608 -0.0868 0.7224 0.8047
-0.500 0.3056 0.02289 0.01705 -0.0824 0.7159 0.8118
-0.250 0.3320 0.02302 0.01711 -0.0822 0.7134 0.8219
0.000 0.3552 0.02303 0.01710 -0.0805 0.7115 0.8284
0.250 0.3871 0.02295 0.01694 -0.0809 0.7101 0.8375
0.500 0.4142 0.02288 0.01683 -0.0800 0.7087 0.8436
0.750 0.3925 0.02455 0.01862 -0.0736 0.6975 0.8537
1.000 0.4189 0.02435 0.01839 -0.0727 0.6956 0.8597
1.250 0.4513 0.02409 0.01808 -0.0730 0.6942 0.8662
1.500 0.4882 0.02377 0.01770 -0.0743 0.6930 0.8720
1.750 0.5186 0.02356 0.01745 -0.0743 0.6916 0.8765
2.000 0.4944 0.02522 0.01923 -0.0676 0.6792 0.8862
2.250 0.5285 0.02476 0.01874 -0.0681 0.6780 0.8900
2.500 0.5030 0.02646 0.02052 -0.0611 0.6663 0.8991
2.750 0.5386 0.02610 0.02014 -0.0623 0.6642 0.9032
3.000 0.5751 0.02558 0.01960 -0.0632 0.6629 0.9069
3.250 0.6149 0.02500 0.01900 -0.0648 0.6618 0.9106
3.500 0.6578 0.02439 0.01835 -0.0670 0.6609 0.9140
3.750 0.7009 0.02381 0.01775 -0.0694 0.6598 0.9173
4.000 0.6706 0.02528 0.01934 -0.0611 0.6470 0.9276
4.250 0.7165 0.02456 0.01860 -0.0638 0.6461 0.9306
4.500 0.7591 0.02379 0.01784 -0.0657 0.6449 0.9338
4.750 0.8026 0.02304 0.01707 -0.0679 0.6438 0.9371
5.000 0.7811 0.02424 0.01838 -0.0611 0.6319 0.9487
5.250 0.8284 0.02338 0.01753 -0.0638 0.6305 0.9522
5.500 0.8760 0.02248 0.01663 -0.0666 0.6291 0.9557
5.750 0.9249 0.02161 0.01575 -0.0698 0.6277 0.9588
6.000 0.9249 0.02237 0.01665 -0.0664 0.6172 0.9712
6.250 0.9763 0.02145 0.01574 -0.0701 0.6148 0.9737
6.500 1.0299 0.02050 0.01479 -0.0741 0.6126 0.9760
6.750 1.0529 0.02079 0.01521 -0.0745 0.6036 0.9887
7.000 1.1002 0.01998 0.01443 -0.0777 0.5991 0.9981
7.250 1.1526 0.01902 0.01344 -0.0816 0.5957 1.0000
7.500 1.1509 0.01940 0.01394 -0.0777 0.5851 1.0000
7.750 1.2002 0.01850 0.01301 -0.0810 0.5803 1.0000
8.000 1.2050 0.01881 0.01343 -0.0781 0.5691 1.0000
8.250 1.2269 0.01872 0.01340 -0.0775 0.5595 1.0000
8.500 1.2621 0.01823 0.01290 -0.0788 0.5500 1.0000
8.750 1.2736 0.01855 0.01328 -0.0769 0.5368 1.0000
9.000 1.2900 0.01878 0.01352 -0.0757 0.5225 1.0000
9.250 1.3073 0.01905 0.01378 -0.0747 0.5071 1.0000
9.500 1.3236 0.01943 0.01411 -0.0735 0.4903 1.0000
9.750 1.3369 0.01998 0.01460 -0.0720 0.4722 1.0000
10.000 1.3437 0.02089 0.01547 -0.0698 0.4532 1.0000
10.250 1.3501 0.02191 0.01641 -0.0677 0.4335 1.0000
10.500 1.3560 0.02303 0.01745 -0.0657 0.4143 1.0000
10.750 1.3608 0.02428 0.01859 -0.0636 0.3955 1.0000
11.000 1.3637 0.02569 0.01993 -0.0615 0.3771 1.0000
11.250 1.3654 0.02724 0.02143 -0.0595 0.3590 1.0000
11.500 1.3671 0.02887 0.02301 -0.0575 0.3416 1.0000
11.750 1.3686 0.03056 0.02465 -0.0557 0.3247 1.0000
12.000 1.3699 0.03233 0.02638 -0.0540 0.3083 1.0000
12.250 1.3712 0.03416 0.02817 -0.0524 0.2925 1.0000
12.500 1.3727 0.03606 0.03002 -0.0509 0.2773 1.0000
12.750 1.3742 0.03802 0.03195 -0.0495 0.2625 1.0000
13.000 1.3756 0.04007 0.03396 -0.0483 0.2483 1.0000
13.250 1.3771 0.04218 0.03603 -0.0472 0.2346 1.0000
13.500 1.3782 0.04439 0.03820 -0.0461 0.2216 1.0000
13.750 1.3800 0.04663 0.04044 -0.0452 0.2087 1.0000
14.000 1.3824 0.04889 0.04271 -0.0445 0.1962 1.0000
14.250 1.3842 0.05126 0.04508 -0.0438 0.1845 1.0000
14.500 1.3854 0.05374 0.04755 -0.0432 0.1735 1.0000
14.750 1.3856 0.05637 0.05013 -0.0426 0.1634 1.0000
15.000 1.3878 0.05892 0.05274 -0.0423 0.1528 1.0000
15.250 1.3892 0.06158 0.05543 -0.0419 0.1432 1.0000
15.500 1.3881 0.06455 0.05833 -0.0417 0.1346 1.0000
15.750 1.3900 0.06733 0.06120 -0.0416 0.1256 1.0000
16.000 1.3901 0.07032 0.06421 -0.0416 0.1177 1.0000
16.250 1.3893 0.07349 0.06738 -0.0417 0.1103 1.0000
16.500 1.3903 0.07652 0.07048 -0.0418 0.1031 1.0000
16.750 1.3883 0.07991 0.07383 -0.0421 0.0969 1.0000
17.000 1.3892 0.08309 0.07714 -0.0425 0.0905 1.0000
17.250 1.3875 0.08656 0.08058 -0.0429 0.0853 1.0000
17.500 1.3878 0.08990 0.08403 -0.0435 0.0800 1.0000
17.750 1.3864 0.09349 0.08765 -0.0442 0.0753 1.0000
18.000 1.3862 0.09686 0.09107 -0.0448 0.0709 1.0000
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