E203 (13.64%) (e203-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E203 (13.64%) (e203-il) Reynolds number: 1,000,000 Max Cl/Cd: 132.39 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e203-il-1000000.txt Download as CSV file: xf-e203-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E203 (13.64%)
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
------ -------- --------- --------- -------- -------- --------
-15.000 -0.6868 0.09262 0.09058 -0.0485 1.0000 0.0095
-14.750 -0.7354 0.07861 0.07638 -0.0569 1.0000 0.0093
-14.500 -0.7456 0.07279 0.07047 -0.0606 1.0000 0.0095
-14.250 -0.7775 0.06393 0.06144 -0.0661 1.0000 0.0093
-14.000 -0.7957 0.05785 0.05524 -0.0698 1.0000 0.0092
-13.750 -0.8134 0.05221 0.04946 -0.0731 1.0000 0.0093
-13.500 -0.8291 0.04719 0.04429 -0.0758 1.0000 0.0093
-13.250 -0.8291 0.04447 0.04150 -0.0772 1.0000 0.0096
-13.000 -0.8426 0.04036 0.03724 -0.0788 1.0000 0.0096
-12.750 -0.8520 0.03715 0.03390 -0.0795 1.0000 0.0096
-12.500 -0.8592 0.03465 0.03129 -0.0794 1.0000 0.0097
-12.250 -0.8704 0.03242 0.02893 -0.0780 1.0000 0.0098
-12.000 -0.8824 0.03111 0.02753 -0.0749 1.0000 0.0099
-11.750 -0.9029 0.02993 0.02626 -0.0692 1.0000 0.0098
-11.500 -0.8988 0.02905 0.02529 -0.0669 0.9997 0.0100
-11.250 -0.8707 0.02770 0.02378 -0.0693 0.9976 0.0101
-11.000 -0.8537 0.02388 0.01964 -0.0716 0.9947 0.0105
-10.750 -0.8289 0.02217 0.01784 -0.0731 0.9921 0.0108
-10.500 -0.8007 0.02110 0.01671 -0.0746 0.9892 0.0112
-10.250 -0.7699 0.02015 0.01570 -0.0765 0.9869 0.0115
-10.000 -0.7376 0.01919 0.01465 -0.0785 0.9851 0.0119
-9.750 -0.7044 0.01822 0.01360 -0.0806 0.9837 0.0122
-9.500 -0.6781 0.01744 0.01274 -0.0810 0.9793 0.0126
-9.250 -0.6468 0.01674 0.01198 -0.0824 0.9760 0.0130
-9.000 -0.6126 0.01611 0.01128 -0.0842 0.9737 0.0133
-8.750 -0.5784 0.01541 0.01050 -0.0861 0.9714 0.0135
-8.500 -0.5600 0.01395 0.00893 -0.0852 0.9619 0.0141
-8.250 -0.5328 0.01309 0.00801 -0.0857 0.9543 0.0146
-8.000 -0.5052 0.01249 0.00736 -0.0861 0.9438 0.0151
-7.750 -0.4772 0.01196 0.00675 -0.0864 0.9295 0.0157
-7.500 -0.4491 0.01154 0.00625 -0.0866 0.9111 0.0163
-7.250 -0.4230 0.01121 0.00579 -0.0864 0.8888 0.0170
-7.000 -0.3981 0.01092 0.00537 -0.0859 0.8672 0.0173
-6.750 -0.3739 0.01059 0.00491 -0.0853 0.8466 0.0178
-6.500 -0.3503 0.01018 0.00435 -0.0846 0.8273 0.0190
-6.250 -0.3253 0.00992 0.00399 -0.0841 0.8103 0.0202
-6.000 -0.2999 0.00971 0.00369 -0.0837 0.7947 0.0216
-5.750 -0.2741 0.00950 0.00339 -0.0833 0.7802 0.0238
-5.500 -0.2487 0.00919 0.00308 -0.0830 0.7667 0.0329
-5.250 -0.2240 0.00874 0.00276 -0.0826 0.7546 0.0670
-5.000 -0.1982 0.00846 0.00254 -0.0824 0.7432 0.0944
-4.750 -0.1723 0.00821 0.00234 -0.0822 0.7324 0.1227
-4.500 -0.1459 0.00794 0.00215 -0.0821 0.7223 0.1547
-4.250 -0.1197 0.00765 0.00198 -0.0819 0.7133 0.1962
-4.000 -0.0935 0.00737 0.00182 -0.0818 0.7041 0.2417
-3.750 -0.0670 0.00707 0.00167 -0.0818 0.6960 0.2915
-3.500 -0.0405 0.00684 0.00157 -0.0817 0.6881 0.3427
-3.250 -0.0129 0.00672 0.00151 -0.0817 0.6807 0.3763
-3.000 0.0147 0.00666 0.00147 -0.0816 0.6734 0.4056
-2.750 0.0428 0.00661 0.00145 -0.0817 0.6668 0.4244
-2.500 0.0709 0.00661 0.00142 -0.0817 0.6602 0.4378
-2.250 0.0990 0.00661 0.00140 -0.0818 0.6540 0.4510
-2.000 0.1272 0.00658 0.00138 -0.0818 0.6477 0.4603
-1.750 0.1553 0.00661 0.00135 -0.0819 0.6419 0.4682
-1.500 0.1837 0.00659 0.00134 -0.0820 0.6363 0.4768
-1.250 0.2120 0.00660 0.00133 -0.0820 0.6305 0.4845
-1.000 0.2400 0.00662 0.00132 -0.0821 0.6251 0.4926
-0.750 0.2685 0.00661 0.00132 -0.0822 0.6198 0.5003
-0.500 0.2966 0.00662 0.00132 -0.0822 0.6142 0.5084
-0.250 0.3248 0.00664 0.00133 -0.0823 0.6092 0.5162
0.000 0.3532 0.00663 0.00134 -0.0824 0.6040 0.5245
0.250 0.3812 0.00665 0.00136 -0.0824 0.5988 0.5324
0.500 0.4093 0.00667 0.00138 -0.0825 0.5939 0.5415
0.750 0.4376 0.00666 0.00141 -0.0826 0.5887 0.5514
1.000 0.4655 0.00668 0.00144 -0.0826 0.5835 0.5618
1.250 0.4935 0.00670 0.00148 -0.0826 0.5785 0.5726
1.500 0.5217 0.00669 0.00152 -0.0827 0.5731 0.5840
1.750 0.5493 0.00673 0.00156 -0.0827 0.5674 0.5961
2.000 0.5774 0.00673 0.00161 -0.0827 0.5613 0.6098
2.250 0.6049 0.00674 0.00166 -0.0827 0.5543 0.6252
2.500 0.6325 0.00676 0.00172 -0.0826 0.5480 0.6422
2.750 0.6602 0.00676 0.00179 -0.0826 0.5413 0.6609
3.000 0.6873 0.00679 0.00186 -0.0825 0.5346 0.6824
3.250 0.7147 0.00678 0.00194 -0.0824 0.5272 0.7067
3.500 0.7414 0.00680 0.00203 -0.0822 0.5195 0.7336
3.750 0.7683 0.00679 0.00212 -0.0820 0.5116 0.7636
4.000 0.7943 0.00681 0.00222 -0.0816 0.5037 0.7977
4.250 0.8197 0.00679 0.00233 -0.0811 0.4949 0.8381
4.500 0.8432 0.00677 0.00245 -0.0801 0.4858 0.8869
4.750 0.8663 0.00677 0.00256 -0.0789 0.4754 0.9504
5.000 0.9061 0.00689 0.00267 -0.0816 0.4614 1.0000
5.250 0.9319 0.00705 0.00279 -0.0813 0.4475 1.0000
5.500 0.9572 0.00723 0.00293 -0.0809 0.4305 1.0000
5.750 0.9822 0.00744 0.00309 -0.0804 0.4109 1.0000
6.000 1.0054 0.00776 0.00329 -0.0797 0.3812 1.0000
6.250 1.0264 0.00824 0.00358 -0.0786 0.3393 1.0000
6.500 1.0452 0.00886 0.00395 -0.0771 0.2894 1.0000
6.750 1.0622 0.00960 0.00441 -0.0755 0.2373 1.0000
7.000 1.0793 0.01031 0.00487 -0.0738 0.1914 1.0000
7.250 1.0967 0.01097 0.00533 -0.0722 0.1548 1.0000
7.500 1.1146 0.01157 0.00578 -0.0706 0.1254 1.0000
7.750 1.1326 0.01214 0.00621 -0.0691 0.1024 1.0000
8.000 1.1509 0.01266 0.00664 -0.0676 0.0837 1.0000
8.250 1.1681 0.01321 0.00711 -0.0660 0.0676 1.0000
8.500 1.1846 0.01376 0.00758 -0.0642 0.0541 1.0000
8.750 1.1989 0.01430 0.00806 -0.0620 0.0424 1.0000
9.000 1.2112 0.01487 0.00858 -0.0595 0.0322 1.0000
9.250 1.2195 0.01563 0.00925 -0.0563 0.0200 1.0000
9.500 1.2273 0.01645 0.01001 -0.0532 0.0124 1.0000
9.750 1.2399 0.01707 0.01067 -0.0510 0.0106 1.0000
10.000 1.2504 0.01782 0.01145 -0.0485 0.0093 1.0000
10.250 1.2628 0.01849 0.01216 -0.0464 0.0088 1.0000
10.500 1.2748 0.01921 0.01293 -0.0444 0.0084 1.0000
10.750 1.2856 0.02001 0.01379 -0.0424 0.0080 1.0000
11.000 1.2955 0.02091 0.01473 -0.0403 0.0076 1.0000
11.250 1.3026 0.02202 0.01590 -0.0382 0.0072 1.0000
11.500 1.3068 0.02340 0.01736 -0.0358 0.0069 1.0000
11.750 1.3120 0.02480 0.01885 -0.0339 0.0067 1.0000
12.000 1.3198 0.02608 0.02019 -0.0323 0.0066 1.0000
12.250 1.3265 0.02751 0.02169 -0.0309 0.0065 1.0000
12.500 1.3324 0.02908 0.02334 -0.0295 0.0064 1.0000
12.750 1.3401 0.03055 0.02488 -0.0284 0.0062 1.0000
13.000 1.3443 0.03239 0.02680 -0.0273 0.0060 1.0000
13.250 1.3485 0.03430 0.02878 -0.0263 0.0060 1.0000
13.500 1.3523 0.03630 0.03087 -0.0254 0.0059 1.0000
13.750 1.3542 0.03856 0.03321 -0.0246 0.0058 1.0000
14.000 1.3575 0.04076 0.03548 -0.0241 0.0055 1.0000
14.250 1.3584 0.04325 0.03807 -0.0236 0.0057 1.0000
14.500 1.3616 0.04559 0.04046 -0.0233 0.0054 1.0000
14.750 1.3594 0.04859 0.04356 -0.0231 0.0053 1.0000
15.000 1.3581 0.05159 0.04664 -0.0230 0.0052 1.0000
15.250 1.3563 0.05474 0.04988 -0.0232 0.0051 1.0000
15.500 1.3516 0.05837 0.05361 -0.0235 0.0051 1.0000
15.750 1.3502 0.06169 0.05701 -0.0239 0.0051 1.0000
16.000 1.3313 0.06736 0.06283 -0.0247 0.0049 1.0000
16.250 1.3230 0.07185 0.06744 -0.0256 0.0048 1.0000
16.500 1.3198 0.07579 0.07149 -0.0266 0.0048 1.0000
16.750 1.3182 0.07964 0.07543 -0.0278 0.0048 1.0000
17.000 1.3150 0.08382 0.07971 -0.0292 0.0048 1.0000
17.250 1.3111 0.08817 0.08417 -0.0307 0.0048 1.0000
17.500 1.3060 0.09284 0.08895 -0.0324 0.0047 1.0000
17.750 1.3019 0.09750 0.09372 -0.0343 0.0047 1.0000
18.000 1.2957 0.10257 0.09891 -0.0365 0.0047 1.0000
18.250 1.2899 0.10766 0.10411 -0.0388 0.0047 1.0000
18.500 1.2838 0.11294 0.10951 -0.0413 0.0047 1.0000
18.750 1.2770 0.11840 0.11508 -0.0440 0.0047 1.0000
19.000 1.2682 0.12437 0.12117 -0.0471 0.0047 1.0000
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