E193 (10.22%) (e193-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E193 (10.22%) (e193-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.53 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e193-il-1000000-n5.txt Download as CSV file: xf-e193-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E193 (10.22%)
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3867 0.08730 0.08569 -0.0368 1.0000 0.0059
-9.250 -0.3840 0.08220 0.08059 -0.0405 0.9857 0.0058
-8.750 -0.5101 0.02641 0.02339 -0.0853 0.8537 0.0052
-8.500 -0.5013 0.02313 0.01962 -0.0843 0.8298 0.0053
-8.250 -0.4859 0.02096 0.01706 -0.0834 0.8099 0.0055
-8.000 -0.4675 0.01921 0.01496 -0.0826 0.7927 0.0056
-7.750 -0.4467 0.01786 0.01332 -0.0820 0.7777 0.0058
-7.500 -0.4242 0.01682 0.01204 -0.0814 0.7637 0.0059
-7.250 -0.4010 0.01589 0.01089 -0.0809 0.7506 0.0061
-7.000 -0.3767 0.01515 0.00996 -0.0805 0.7387 0.0062
-6.750 -0.3519 0.01449 0.00915 -0.0801 0.7280 0.0063
-6.500 -0.3267 0.01392 0.00841 -0.0798 0.7179 0.0064
-6.000 -0.2763 0.01264 0.00685 -0.0791 0.6990 0.0065
-5.750 -0.2517 0.01181 0.00587 -0.0786 0.6909 0.0067
-5.500 -0.2259 0.01129 0.00525 -0.0783 0.6826 0.0069
-5.250 -0.1997 0.01087 0.00473 -0.0781 0.6751 0.0071
-5.000 -0.1730 0.01055 0.00435 -0.0779 0.6678 0.0073
-4.750 -0.1463 0.01026 0.00400 -0.0777 0.6609 0.0077
-4.500 -0.1193 0.00998 0.00366 -0.0776 0.6542 0.0080
-4.000 -0.0652 0.00943 0.00297 -0.0772 0.6419 0.0086
-3.750 -0.0380 0.00921 0.00268 -0.0771 0.6357 0.0089
-3.500 -0.0105 0.00903 0.00245 -0.0770 0.6303 0.0092
-3.250 0.0169 0.00882 0.00219 -0.0769 0.6247 0.0096
-3.000 0.0443 0.00863 0.00194 -0.0767 0.6192 0.0103
-2.750 0.0719 0.00849 0.00176 -0.0767 0.6141 0.0111
-2.500 0.0997 0.00837 0.00160 -0.0766 0.6087 0.0121
-2.000 0.1546 0.00802 0.00133 -0.0765 0.5989 0.0402
-1.750 0.1821 0.00786 0.00123 -0.0764 0.5938 0.0629
-1.250 0.2370 0.00755 0.00109 -0.0764 0.5844 0.1302
-1.000 0.2643 0.00736 0.00104 -0.0764 0.5793 0.1795
-0.750 0.2913 0.00718 0.00101 -0.0763 0.5746 0.2391
-0.500 0.3187 0.00700 0.00099 -0.0763 0.5701 0.2979
-0.250 0.3459 0.00681 0.00098 -0.0763 0.5651 0.3646
0.000 0.3729 0.00667 0.00098 -0.0762 0.5603 0.4268
0.250 0.4003 0.00655 0.00099 -0.0762 0.5558 0.4778
0.500 0.4274 0.00641 0.00101 -0.0761 0.5507 0.5424
0.750 0.4539 0.00625 0.00105 -0.0759 0.5458 0.6182
1.000 0.4803 0.00608 0.00108 -0.0756 0.5413 0.6944
1.250 0.5057 0.00590 0.00113 -0.0751 0.5359 0.7756
1.500 0.5290 0.00571 0.00120 -0.0739 0.5304 0.8666
1.750 0.5611 0.00561 0.00127 -0.0746 0.5238 0.9610
2.500 0.6700 0.00584 0.00139 -0.0803 0.4981 1.0000
2.750 0.6956 0.00594 0.00145 -0.0799 0.4890 1.0000
3.000 0.7213 0.00603 0.00152 -0.0795 0.4796 1.0000
3.250 0.7468 0.00615 0.00160 -0.0790 0.4688 1.0000
3.500 0.7723 0.00628 0.00168 -0.0786 0.4570 1.0000
3.750 0.7980 0.00641 0.00178 -0.0781 0.4444 1.0000
4.000 0.8235 0.00656 0.00189 -0.0777 0.4303 1.0000
4.250 0.8484 0.00677 0.00202 -0.0772 0.4084 1.0000
4.500 0.8715 0.00714 0.00221 -0.0764 0.3696 1.0000
4.750 0.8946 0.00752 0.00244 -0.0757 0.3324 1.0000
5.000 0.9151 0.00815 0.00278 -0.0746 0.2745 1.0000
5.250 0.9337 0.00894 0.00322 -0.0732 0.2066 1.0000
5.500 0.9539 0.00959 0.00362 -0.0721 0.1579 1.0000
5.750 0.9747 0.01018 0.00401 -0.0711 0.1190 1.0000
6.000 0.9961 0.01070 0.00438 -0.0701 0.0884 1.0000
6.250 1.0180 0.01118 0.00475 -0.0692 0.0662 1.0000
6.500 1.0382 0.01177 0.00519 -0.0681 0.0400 1.0000
6.750 1.0590 0.01230 0.00564 -0.0671 0.0231 1.0000
7.000 1.0789 0.01290 0.00615 -0.0659 0.0091 1.0000
7.250 1.1013 0.01327 0.00653 -0.0651 0.0079 1.0000
7.500 1.1232 0.01367 0.00696 -0.0642 0.0067 1.0000
7.750 1.1451 0.01405 0.00736 -0.0633 0.0064 1.0000
8.000 1.1667 0.01443 0.00779 -0.0624 0.0061 1.0000
8.250 1.1877 0.01484 0.00823 -0.0615 0.0058 1.0000
8.500 1.2077 0.01529 0.00872 -0.0603 0.0055 1.0000
8.750 1.2272 0.01575 0.00922 -0.0591 0.0053 1.0000
9.000 1.2455 0.01626 0.00978 -0.0577 0.0052 1.0000
9.250 1.2627 0.01681 0.01038 -0.0562 0.0050 1.0000
9.500 1.2771 0.01739 0.01100 -0.0542 0.0048 1.0000
9.750 1.2889 0.01802 0.01169 -0.0517 0.0047 1.0000
10.000 1.2986 0.01878 0.01251 -0.0490 0.0045 1.0000
10.250 1.3060 0.01970 0.01351 -0.0462 0.0044 1.0000
10.500 1.3148 0.02059 0.01447 -0.0437 0.0043 1.0000
10.750 1.3254 0.02141 0.01536 -0.0417 0.0042 1.0000
11.000 1.3342 0.02239 0.01641 -0.0396 0.0042 1.0000
11.250 1.3440 0.02336 0.01745 -0.0378 0.0041 1.0000
11.500 1.3542 0.02436 0.01851 -0.0363 0.0040 1.0000
11.750 1.3585 0.02585 0.02009 -0.0343 0.0040 1.0000
12.000 1.3689 0.02695 0.02125 -0.0331 0.0039 1.0000
12.250 1.3759 0.02838 0.02276 -0.0317 0.0038 1.0000
12.500 1.3803 0.03011 0.02458 -0.0304 0.0037 1.0000
12.750 1.3864 0.03176 0.02632 -0.0293 0.0036 1.0000
13.000 1.3902 0.03370 0.02835 -0.0283 0.0036 1.0000
13.250 1.3947 0.03565 0.03038 -0.0275 0.0035 1.0000
13.500 1.3962 0.03795 0.03278 -0.0267 0.0035 1.0000
13.750 1.3992 0.04018 0.03510 -0.0262 0.0034 1.0000
14.000 1.4002 0.04268 0.03769 -0.0257 0.0033 1.0000
14.250 1.4004 0.04533 0.04045 -0.0254 0.0034 1.0000
14.500 1.4034 0.04775 0.04294 -0.0253 0.0033 1.0000
14.750 1.3998 0.05101 0.04632 -0.0252 0.0033 1.0000
15.000 1.4026 0.05361 0.04900 -0.0254 0.0032 1.0000
15.250 1.3995 0.05704 0.05254 -0.0257 0.0032 1.0000
15.500 1.3980 0.06037 0.05598 -0.0262 0.0032 1.0000
15.750 1.3941 0.06415 0.05987 -0.0269 0.0031 1.0000
16.000 1.3887 0.06828 0.06411 -0.0279 0.0031 1.0000
16.250 1.3845 0.07236 0.06830 -0.0290 0.0031 1.0000
16.500 1.3818 0.07636 0.07239 -0.0303 0.0030 1.0000
16.750 1.3747 0.08115 0.07730 -0.0319 0.0030 1.0000
17.000 1.3664 0.08631 0.08259 -0.0338 0.0031 1.0000
17.250 1.3605 0.09121 0.08760 -0.0358 0.0030 1.0000
17.500 1.3538 0.09638 0.09287 -0.0380 0.0030 1.0000
17.750 1.3403 0.10292 0.09956 -0.0409 0.0030 1.0000
18.000 1.3333 0.10847 0.10521 -0.0436 0.0030 1.0000
18.250 1.3224 0.11483 0.11170 -0.0467 0.0030 1.0000
18.500 1.3111 0.12147 0.11846 -0.0501 0.0030 1.0000
18.750 1.3014 0.12796 0.12506 -0.0536 0.0029 1.0000
19.000 1.2900 0.13492 0.13214 -0.0575 0.0029 1.0000
19.250 1.2795 0.14182 0.13915 -0.0615 0.0029 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E193 (10.22%) (e193-il)