E392 (10.15%) (e392-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: E392 (10.15%) (e392-il) Reynolds number: 100,000 Max Cl/Cd: 61.79 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e392-il-100000-n5.txt Download as CSV file: xf-e392-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E392 (10.15%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3259 0.08729 0.08269 -0.0412 1.0000 0.0355
-7.500 -0.3552 0.08001 0.07571 -0.0417 1.0000 0.0280
-7.250 -0.3577 0.07749 0.07326 -0.0414 0.9979 0.0274
-7.000 -0.3350 0.07163 0.06738 -0.0500 0.9853 0.0263
-6.750 -0.3112 0.06409 0.05977 -0.0616 0.9716 0.0250
-6.250 -0.2635 0.04320 0.03794 -0.0853 0.9413 0.0216
-6.000 -0.2367 0.03812 0.03236 -0.0897 0.9299 0.0215
-5.750 -0.2097 0.03365 0.02731 -0.0926 0.9179 0.0214
-5.500 -0.1806 0.03001 0.02305 -0.0947 0.9069 0.0215
-5.250 -0.1494 0.02699 0.01940 -0.0963 0.8973 0.0218
-5.000 -0.1195 0.02487 0.01701 -0.0975 0.8871 0.0230
-4.750 -0.0904 0.02352 0.01540 -0.0981 0.8760 0.0251
-4.500 -0.0603 0.02198 0.01347 -0.0985 0.8659 0.0273
-4.250 -0.0300 0.02045 0.01165 -0.0987 0.8566 0.0288
-4.000 -0.0029 0.01924 0.01035 -0.0987 0.8456 0.0310
-3.750 0.0252 0.01832 0.00929 -0.0986 0.8355 0.0352
-3.500 0.0538 0.01750 0.00834 -0.0987 0.8266 0.0445
-3.250 0.0810 0.01668 0.00747 -0.0986 0.8162 0.0636
-3.000 0.1084 0.01595 0.00693 -0.0987 0.8070 0.1113
-2.750 0.1360 0.01526 0.00645 -0.0989 0.7986 0.1807
-2.500 0.1622 0.01467 0.00614 -0.0989 0.7891 0.2794
-2.250 0.1885 0.01413 0.00597 -0.0987 0.7814 0.4105
-2.000 0.2132 0.01380 0.00592 -0.0979 0.7725 0.5243
-1.750 0.2380 0.01359 0.00585 -0.0969 0.7649 0.6136
-1.500 0.2617 0.01342 0.00578 -0.0955 0.7570 0.6897
-1.250 0.2839 0.01328 0.00572 -0.0937 0.7496 0.7612
-1.000 0.3058 0.01313 0.00563 -0.0916 0.7423 0.8350
-0.750 0.3376 0.01296 0.00542 -0.0917 0.7354 0.9270
-0.500 0.3757 0.01294 0.00522 -0.0939 0.7281 1.0000
-0.250 0.4035 0.01308 0.00516 -0.0940 0.7214 1.0000
0.000 0.4309 0.01322 0.00514 -0.0941 0.7142 1.0000
0.250 0.4588 0.01336 0.00512 -0.0942 0.7080 1.0000
0.500 0.4859 0.01353 0.00518 -0.0942 0.7008 1.0000
0.750 0.5140 0.01368 0.00518 -0.0942 0.6953 1.0000
1.000 0.5406 0.01387 0.00532 -0.0942 0.6878 1.0000
1.250 0.5684 0.01404 0.00538 -0.0942 0.6820 1.0000
1.500 0.5953 0.01424 0.00553 -0.0941 0.6753 1.0000
1.750 0.6227 0.01443 0.00567 -0.0941 0.6690 1.0000
2.000 0.6499 0.01463 0.00583 -0.0940 0.6631 1.0000
2.250 0.6767 0.01485 0.00603 -0.0939 0.6563 1.0000
2.500 0.7045 0.01503 0.00615 -0.0939 0.6511 1.0000
2.750 0.7305 0.01529 0.00647 -0.0937 0.6437 1.0000
3.000 0.7580 0.01548 0.00664 -0.0937 0.6380 1.0000
3.250 0.7841 0.01574 0.00695 -0.0935 0.6308 1.0000
3.500 0.8111 0.01595 0.00720 -0.0933 0.6245 1.0000
3.750 0.8372 0.01620 0.00750 -0.0931 0.6172 1.0000
4.000 0.8639 0.01641 0.00774 -0.0929 0.6099 1.0000
4.250 0.8896 0.01664 0.00805 -0.0925 0.6016 1.0000
4.500 0.9165 0.01680 0.00825 -0.0922 0.5937 1.0000
4.750 0.9413 0.01704 0.00861 -0.0918 0.5837 1.0000
5.000 0.9670 0.01722 0.00887 -0.0913 0.5741 1.0000
5.250 0.9932 0.01735 0.00908 -0.0908 0.5643 1.0000
5.500 1.0175 0.01755 0.00941 -0.0902 0.5521 1.0000
5.750 1.0419 0.01773 0.00970 -0.0895 0.5393 1.0000
6.000 1.0661 0.01790 0.00999 -0.0888 0.5255 1.0000
6.250 1.0900 0.01807 0.01030 -0.0880 0.5103 1.0000
6.500 1.1135 0.01825 0.01057 -0.0871 0.4935 1.0000
6.750 1.1358 0.01848 0.01093 -0.0861 0.4731 1.0000
7.000 1.1573 0.01873 0.01124 -0.0849 0.4494 1.0000
7.250 1.1773 0.01909 0.01166 -0.0835 0.4196 1.0000
7.500 1.1950 0.01958 0.01214 -0.0818 0.3796 1.0000
7.750 1.2072 0.02045 0.01272 -0.0795 0.3194 1.0000
8.000 1.2125 0.02189 0.01370 -0.0765 0.2513 1.0000
8.250 1.2163 0.02355 0.01496 -0.0737 0.1923 1.0000
8.500 1.2202 0.02520 0.01630 -0.0710 0.1451 1.0000
8.750 1.2251 0.02668 0.01762 -0.0683 0.1140 1.0000
9.000 1.2292 0.02813 0.01898 -0.0656 0.0901 1.0000
9.250 1.2320 0.02976 0.02053 -0.0629 0.0686 1.0000
9.500 1.2326 0.03165 0.02235 -0.0603 0.0526 1.0000
9.750 1.2333 0.03365 0.02431 -0.0580 0.0429 1.0000
10.000 1.2363 0.03557 0.02635 -0.0561 0.0368 1.0000
10.250 1.2361 0.03787 0.02869 -0.0544 0.0336 1.0000
10.500 1.2383 0.04007 0.03105 -0.0529 0.0315 1.0000
10.750 1.2406 0.04236 0.03350 -0.0516 0.0297 1.0000
11.000 1.2428 0.04474 0.03602 -0.0505 0.0283 1.0000
11.250 1.2450 0.04722 0.03863 -0.0495 0.0272 1.0000
11.500 1.2463 0.04986 0.04137 -0.0487 0.0261 1.0000
11.750 1.2469 0.05270 0.04426 -0.0478 0.0252 1.0000
12.000 1.2532 0.05504 0.04683 -0.0471 0.0242 1.0000
12.250 1.2590 0.05750 0.04948 -0.0464 0.0230 1.0000
12.500 1.2640 0.06008 0.05224 -0.0459 0.0220 1.0000
12.750 1.2690 0.06279 0.05511 -0.0453 0.0213 1.0000
13.000 1.2737 0.06563 0.05811 -0.0449 0.0208 1.0000
13.250 1.2774 0.06864 0.06130 -0.0446 0.0203 1.0000
13.500 1.2801 0.07186 0.06468 -0.0444 0.0199 1.0000
13.750 1.2814 0.07535 0.06834 -0.0444 0.0195 1.0000
14.000 1.2810 0.07916 0.07234 -0.0446 0.0193 1.0000
14.250 1.2783 0.08341 0.07679 -0.0450 0.0190 1.0000
14.500 1.2718 0.08821 0.08181 -0.0460 0.0188 1.0000
14.750 1.2612 0.09357 0.08746 -0.0477 0.0187 1.0000
15.000 1.2489 0.09939 0.09357 -0.0500 0.0186 1.0000
15.250 1.2349 0.10578 0.10025 -0.0529 0.0185 1.0000
15.500 1.2198 0.11269 0.10741 -0.0565 0.0185 1.0000
15.750 1.2040 0.12013 0.11505 -0.0607 0.0185 1.0000
16.000 1.1875 0.12819 0.12332 -0.0656 0.0185 1.0000
16.250 1.1708 0.13683 0.13215 -0.0711 0.0186 1.0000
16.500 1.1539 0.14614 0.14161 -0.0773 0.0187 1.0000
16.750 1.1375 0.15600 0.15159 -0.0838 0.0189 1.0000
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Polar data table (+)
Polar graphs
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