E193 (10.22%) (e193-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E193 (10.22%) (e193-il) Reynolds number: 1,000,000 Max Cl/Cd: 138.85 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e193-il-1000000.txt Download as CSV file: xf-e193-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3841 0.11650 0.11480 -0.0282 1.0000 0.0099
-11.000 -0.3878 0.11131 0.10963 -0.0296 1.0000 0.0102
-10.750 -0.3841 0.10815 0.10648 -0.0305 1.0000 0.0103
-10.500 -0.3764 0.10627 0.10461 -0.0307 1.0000 0.0106
-10.250 -0.3733 0.10294 0.10128 -0.0318 1.0000 0.0107
-10.000 -0.3703 0.09962 0.09798 -0.0330 1.0000 0.0108
-9.750 -0.3666 0.09665 0.09503 -0.0339 1.0000 0.0111
-6.750 -0.3061 0.02784 0.02483 -0.0871 0.8468 0.0149
-6.500 -0.2894 0.02573 0.02242 -0.0864 0.8260 0.0155
-6.250 -0.2878 0.01550 0.01069 -0.0827 0.8092 0.0105
-6.000 -0.2645 0.01421 0.00912 -0.0819 0.7938 0.0105
-5.750 -0.2405 0.01326 0.00801 -0.0813 0.7794 0.0109
-5.500 -0.2156 0.01255 0.00715 -0.0809 0.7661 0.0112
-5.250 -0.1901 0.01195 0.00641 -0.0804 0.7537 0.0115
-5.000 -0.1644 0.01138 0.00574 -0.0800 0.7423 0.0118
-4.750 -0.1385 0.01085 0.00510 -0.0796 0.7318 0.0121
-4.500 -0.1126 0.01037 0.00450 -0.0792 0.7220 0.0123
-4.250 -0.0862 0.00994 0.00398 -0.0789 0.7126 0.0125
-4.000 -0.0595 0.00963 0.00359 -0.0786 0.7041 0.0130
-3.750 -0.0326 0.00939 0.00326 -0.0784 0.6957 0.0134
-3.500 -0.0061 0.00893 0.00271 -0.0781 0.6882 0.0139
-3.250 0.0207 0.00860 0.00229 -0.0778 0.6807 0.0150
-3.000 0.0481 0.00839 0.00203 -0.0777 0.6738 0.0165
-2.750 0.0756 0.00825 0.00182 -0.0776 0.6669 0.0179
-2.500 0.1027 0.00795 0.00158 -0.0774 0.6608 0.0388
-2.250 0.1295 0.00763 0.00144 -0.0773 0.6543 0.0890
-2.000 0.1562 0.00739 0.00135 -0.0771 0.6484 0.1416
-1.750 0.1836 0.00719 0.00127 -0.0771 0.6426 0.1883
-1.500 0.2106 0.00699 0.00121 -0.0771 0.6369 0.2441
-1.250 0.2377 0.00679 0.00118 -0.0770 0.6315 0.3080
-1.000 0.2643 0.00649 0.00115 -0.0769 0.6259 0.4038
-0.750 0.2907 0.00628 0.00114 -0.0767 0.6207 0.4899
-0.500 0.3175 0.00607 0.00114 -0.0766 0.6155 0.5666
-0.250 0.3425 0.00574 0.00117 -0.0760 0.6102 0.6894
0.000 0.3659 0.00547 0.00120 -0.0750 0.6052 0.8054
0.250 0.3888 0.00520 0.00127 -0.0735 0.6004 0.9218
0.500 0.4305 0.00522 0.00129 -0.0764 0.5949 0.9758
0.750 0.4739 0.00529 0.00129 -0.0798 0.5896 0.9912
1.000 0.5166 0.00531 0.00128 -0.0831 0.5841 0.9987
1.250 0.5462 0.00536 0.00129 -0.0835 0.5787 1.0000
1.500 0.5717 0.00543 0.00132 -0.0830 0.5732 1.0000
1.750 0.5974 0.00547 0.00135 -0.0826 0.5670 1.0000
2.000 0.6227 0.00557 0.00138 -0.0820 0.5607 1.0000
2.250 0.6488 0.00560 0.00143 -0.0816 0.5540 1.0000
2.500 0.6743 0.00569 0.00147 -0.0811 0.5471 1.0000
2.750 0.7004 0.00575 0.00152 -0.0808 0.5403 1.0000
3.000 0.7260 0.00584 0.00158 -0.0803 0.5330 1.0000
3.250 0.7522 0.00591 0.00165 -0.0800 0.5252 1.0000
3.500 0.7778 0.00602 0.00172 -0.0795 0.5173 1.0000
3.750 0.8042 0.00608 0.00179 -0.0792 0.5090 1.0000
4.000 0.8302 0.00619 0.00188 -0.0789 0.5004 1.0000
4.250 0.8562 0.00630 0.00198 -0.0785 0.4906 1.0000
4.500 0.8825 0.00640 0.00208 -0.0783 0.4808 1.0000
4.750 0.9081 0.00654 0.00219 -0.0779 0.4656 1.0000
5.000 0.9330 0.00675 0.00232 -0.0773 0.4430 1.0000
5.250 0.9573 0.00702 0.00248 -0.0768 0.4144 1.0000
5.500 0.9810 0.00735 0.00268 -0.0761 0.3811 1.0000
5.750 1.0020 0.00790 0.00299 -0.0751 0.3280 1.0000
6.000 1.0220 0.00857 0.00339 -0.0739 0.2724 1.0000
6.250 1.0408 0.00932 0.00385 -0.0726 0.2149 1.0000
6.500 1.0605 0.00999 0.00429 -0.0714 0.1691 1.0000
6.750 1.0799 0.01067 0.00476 -0.0702 0.1285 1.0000
7.000 1.0979 0.01143 0.00529 -0.0688 0.0871 1.0000
7.250 1.1146 0.01229 0.00590 -0.0671 0.0484 1.0000
7.500 1.1297 0.01323 0.00662 -0.0652 0.0164 1.0000
7.750 1.1495 0.01379 0.00717 -0.0640 0.0114 1.0000
8.000 1.1698 0.01428 0.00770 -0.0628 0.0102 1.0000
8.250 1.1884 0.01488 0.00835 -0.0614 0.0092 1.0000
8.500 1.2075 0.01540 0.00893 -0.0601 0.0089 1.0000
8.750 1.2262 0.01592 0.00950 -0.0587 0.0086 1.0000
9.000 1.2433 0.01651 0.01015 -0.0571 0.0084 1.0000
9.250 1.2591 0.01712 0.01082 -0.0553 0.0080 1.0000
9.500 1.2711 0.01776 0.01152 -0.0528 0.0078 1.0000
9.750 1.2812 0.01848 0.01231 -0.0501 0.0076 1.0000
10.000 1.2904 0.01928 0.01316 -0.0474 0.0073 1.0000
10.250 1.2984 0.02018 0.01414 -0.0447 0.0072 1.0000
10.500 1.3036 0.02130 0.01533 -0.0419 0.0070 1.0000
10.750 1.3038 0.02282 0.01694 -0.0388 0.0068 1.0000
11.000 1.2995 0.02479 0.01903 -0.0357 0.0065 1.0000
11.250 1.3006 0.02657 0.02091 -0.0334 0.0064 1.0000
11.500 1.3065 0.02809 0.02251 -0.0318 0.0064 1.0000
11.750 1.3110 0.02980 0.02430 -0.0302 0.0064 1.0000
12.000 1.3196 0.03123 0.02581 -0.0291 0.0063 1.0000
12.250 1.3262 0.03289 0.02755 -0.0281 0.0062 1.0000
12.500 1.3293 0.03496 0.02972 -0.0269 0.0062 1.0000
12.750 1.3346 0.03686 0.03170 -0.0260 0.0061 1.0000
13.000 1.3363 0.03921 0.03415 -0.0249 0.0061 1.0000
13.250 1.3406 0.04133 0.03637 -0.0242 0.0060 1.0000
13.500 1.3427 0.04376 0.03891 -0.0235 0.0060 1.0000
13.750 1.3455 0.04617 0.04141 -0.0230 0.0060 1.0000
14.000 1.3465 0.04882 0.04419 -0.0225 0.0060 1.0000
14.250 1.3471 0.05161 0.04710 -0.0222 0.0059 1.0000
14.500 1.3479 0.05443 0.05004 -0.0223 0.0058 1.0000
14.750 1.3475 0.05747 0.05320 -0.0224 0.0057 1.0000
15.000 1.3442 0.06104 0.05690 -0.0226 0.0056 1.0000
15.250 1.3408 0.06473 0.06072 -0.0231 0.0056 1.0000
15.500 1.3349 0.06889 0.06504 -0.0239 0.0057 1.0000
15.750 1.3283 0.07331 0.06961 -0.0250 0.0056 1.0000
16.000 1.3215 0.07792 0.07436 -0.0264 0.0056 1.0000
16.250 1.3104 0.08341 0.08002 -0.0282 0.0057 1.0000
16.500 1.3014 0.08875 0.08550 -0.0304 0.0056 1.0000
16.750 1.2948 0.09388 0.09073 -0.0328 0.0054 1.0000
17.000 1.2774 0.10119 0.09825 -0.0360 0.0055 1.0000
17.250 1.2598 0.10887 0.10610 -0.0398 0.0056 1.0000
17.500 1.2443 0.11647 0.11387 -0.0439 0.0056 1.0000
17.750 1.2276 0.12465 0.12220 -0.0485 0.0057 1.0000
18.000 1.2142 0.13242 0.13011 -0.0532 0.0055 1.0000
18.250 1.1933 0.14229 0.14015 -0.0592 0.0057 1.0000
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Polar data table (+)
Polar graphs
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