EPPLER 715 AIRFOIL (e715-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 715 AIRFOIL (e715-il) Reynolds number: 1,000,000 Max Cl/Cd: 136.71 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e715-il-1000000.txt Download as CSV file: xf-e715-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 715 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.7415 0.12099 0.11901 -0.0024 1.0000 0.0048
-16.000 -0.7719 0.10934 0.10721 -0.0090 1.0000 0.0046
-15.750 -0.7982 0.09918 0.09691 -0.0150 1.0000 0.0045
-15.500 -0.8241 0.08961 0.08719 -0.0206 1.0000 0.0044
-15.250 -0.8469 0.08104 0.07847 -0.0258 1.0000 0.0044
-15.000 -0.8617 0.07429 0.07160 -0.0299 1.0000 0.0044
-14.750 -0.8799 0.06731 0.06448 -0.0341 1.0000 0.0044
-14.500 -0.8952 0.06140 0.05845 -0.0376 1.0000 0.0044
-14.250 -0.9075 0.05634 0.05327 -0.0404 1.0000 0.0043
-14.000 -0.9218 0.05125 0.04806 -0.0432 1.0000 0.0044
-13.750 -0.9290 0.04728 0.04399 -0.0452 1.0000 0.0044
-13.500 -0.9405 0.04298 0.03957 -0.0472 1.0000 0.0043
-13.250 -0.9324 0.03920 0.03532 -0.0522 0.8354 0.0044
-13.000 -0.9417 0.03613 0.03193 -0.0526 0.7777 0.0044
-12.750 -0.9447 0.03335 0.02895 -0.0534 0.7455 0.0044
-12.500 -0.9502 0.03033 0.02572 -0.0544 0.7232 0.0044
-12.250 -0.9562 0.02782 0.02303 -0.0547 0.7055 0.0044
-12.000 -0.9608 0.02625 0.02130 -0.0525 0.6911 0.0044
-11.750 -0.9563 0.02495 0.01985 -0.0508 0.6788 0.0045
-11.500 -0.9456 0.02374 0.01851 -0.0496 0.6682 0.0045
-11.250 -0.9319 0.02264 0.01727 -0.0486 0.6590 0.0046
-11.000 -0.9162 0.02160 0.01610 -0.0476 0.6502 0.0047
-10.750 -0.8986 0.02065 0.01503 -0.0468 0.6428 0.0048
-10.500 -0.8793 0.01981 0.01407 -0.0461 0.6356 0.0050
-10.250 -0.8586 0.01905 0.01319 -0.0455 0.6291 0.0051
-10.000 -0.8367 0.01837 0.01242 -0.0450 0.6231 0.0053
-9.750 -0.8174 0.01733 0.01124 -0.0443 0.6176 0.0055
-9.500 -0.7960 0.01648 0.01030 -0.0437 0.6129 0.0059
-9.250 -0.7721 0.01591 0.00966 -0.0433 0.6084 0.0062
-9.000 -0.7476 0.01540 0.00909 -0.0430 0.6040 0.0065
-8.750 -0.7226 0.01495 0.00854 -0.0427 0.5997 0.0069
-8.500 -0.6973 0.01449 0.00802 -0.0424 0.5963 0.0072
-8.250 -0.6725 0.01391 0.00737 -0.0421 0.5928 0.0078
-8.000 -0.6470 0.01345 0.00686 -0.0418 0.5893 0.0087
-7.750 -0.6207 0.01310 0.00643 -0.0416 0.5857 0.0097
-7.500 -0.5950 0.01263 0.00593 -0.0414 0.5824 0.0116
-7.250 -0.5686 0.01222 0.00550 -0.0412 0.5797 0.0146
-7.000 -0.5420 0.01186 0.00513 -0.0410 0.5770 0.0182
-6.750 -0.5151 0.01154 0.00480 -0.0409 0.5742 0.0227
-6.500 -0.4880 0.01124 0.00450 -0.0408 0.5715 0.0283
-6.250 -0.4610 0.01096 0.00422 -0.0408 0.5685 0.0356
-6.000 -0.4338 0.01065 0.00395 -0.0407 0.5664 0.0452
-5.750 -0.4064 0.01035 0.00369 -0.0407 0.5641 0.0576
-5.500 -0.3793 0.00999 0.00341 -0.0406 0.5617 0.0771
-5.250 -0.3522 0.00964 0.00316 -0.0406 0.5595 0.1026
-5.000 -0.3250 0.00931 0.00293 -0.0406 0.5573 0.1320
-4.750 -0.2976 0.00901 0.00272 -0.0406 0.5550 0.1633
-4.500 -0.2702 0.00875 0.00254 -0.0406 0.5524 0.1964
-4.250 -0.2426 0.00842 0.00236 -0.0406 0.5508 0.2348
-4.000 -0.2150 0.00809 0.00218 -0.0406 0.5488 0.2789
-3.750 -0.1873 0.00781 0.00204 -0.0407 0.5468 0.3215
-3.500 -0.1591 0.00761 0.00194 -0.0407 0.5449 0.3572
-3.250 -0.1307 0.00748 0.00188 -0.0408 0.5430 0.3880
-3.000 -0.1019 0.00743 0.00185 -0.0409 0.5411 0.4116
-2.750 -0.0731 0.00743 0.00184 -0.0410 0.5388 0.4272
-2.500 -0.0440 0.00746 0.00185 -0.0411 0.5366 0.4392
-2.250 -0.0147 0.00744 0.00184 -0.0412 0.5351 0.4482
-2.000 0.0146 0.00745 0.00183 -0.0414 0.5335 0.4564
-1.750 0.0438 0.00746 0.00184 -0.0415 0.5317 0.4634
-1.500 0.0732 0.00749 0.00183 -0.0417 0.5299 0.4695
-1.250 0.1023 0.00748 0.00183 -0.0419 0.5280 0.4751
-1.000 0.1315 0.00751 0.00183 -0.0420 0.5261 0.4801
-0.750 0.1608 0.00758 0.00185 -0.0422 0.5241 0.4845
-0.500 0.1896 0.00764 0.00188 -0.0423 0.5218 0.4887
-0.250 0.2189 0.00763 0.00190 -0.0425 0.5205 0.4932
0.000 0.2482 0.00765 0.00191 -0.0427 0.5189 0.4975
0.250 0.2776 0.00768 0.00193 -0.0429 0.5171 0.5009
0.500 0.3066 0.00766 0.00193 -0.0430 0.5153 0.5046
0.750 0.3357 0.00766 0.00194 -0.0432 0.5135 0.5080
1.000 0.3648 0.00769 0.00196 -0.0434 0.5116 0.5116
1.250 0.3939 0.00774 0.00200 -0.0436 0.5096 0.5152
1.500 0.4227 0.00782 0.00205 -0.0437 0.5072 0.5184
1.750 0.4517 0.00781 0.00208 -0.0439 0.5055 0.5217
2.000 0.4808 0.00781 0.00211 -0.0441 0.5036 0.5247
2.250 0.5099 0.00781 0.00214 -0.0443 0.5014 0.5276
2.500 0.5390 0.00782 0.00216 -0.0445 0.4989 0.5304
2.750 0.5681 0.00784 0.00218 -0.0446 0.4964 0.5329
3.000 0.5967 0.00785 0.00220 -0.0448 0.4935 0.5362
3.250 0.6254 0.00790 0.00227 -0.0449 0.4906 0.5391
3.500 0.6545 0.00788 0.00231 -0.0451 0.4880 0.5422
3.750 0.6835 0.00789 0.00234 -0.0453 0.4849 0.5453
4.000 0.7124 0.00790 0.00237 -0.0455 0.4817 0.5479
4.250 0.7408 0.00792 0.00241 -0.0456 0.4782 0.5515
4.500 0.7694 0.00795 0.00248 -0.0458 0.4748 0.5551
4.750 0.7983 0.00794 0.00254 -0.0460 0.4712 0.5589
5.000 0.8271 0.00796 0.00259 -0.0462 0.4672 0.5623
5.250 0.8553 0.00801 0.00265 -0.0463 0.4628 0.5665
5.500 0.8839 0.00801 0.00273 -0.0464 0.4581 0.5713
5.750 0.9124 0.00802 0.00280 -0.0466 0.4526 0.5765
6.000 0.9403 0.00809 0.00288 -0.0467 0.4468 0.5821
6.250 0.9688 0.00810 0.00297 -0.0468 0.4403 0.5890
6.500 0.9965 0.00817 0.00307 -0.0469 0.4326 0.5970
6.750 1.0245 0.00821 0.00319 -0.0470 0.4232 0.6085
7.000 1.0517 0.00829 0.00333 -0.0470 0.4114 0.6259
7.250 1.0782 0.00837 0.00350 -0.0469 0.3971 0.6592
7.500 1.0964 0.00802 0.00374 -0.0451 0.3780 0.8867
7.750 1.1376 0.00841 0.00410 -0.0484 0.3447 1.0000
8.000 1.1601 0.00898 0.00452 -0.0478 0.3100 1.0000
8.250 1.1805 0.00972 0.00506 -0.0471 0.2720 1.0000
8.500 1.2009 0.01042 0.00559 -0.0463 0.2387 1.0000
8.750 1.2207 0.01113 0.00615 -0.0454 0.2088 1.0000
9.000 1.2398 0.01184 0.00673 -0.0445 0.1825 1.0000
9.250 1.2582 0.01255 0.00732 -0.0434 0.1587 1.0000
9.500 1.2758 0.01326 0.00793 -0.0423 0.1377 1.0000
9.750 1.2919 0.01401 0.00858 -0.0410 0.1192 1.0000
10.250 1.3185 0.01560 0.01001 -0.0377 0.0887 1.0000
10.500 1.3266 0.01645 0.01082 -0.0353 0.0770 1.0000
10.750 1.3289 0.01732 0.01168 -0.0320 0.0691 1.0000
11.000 1.3304 0.01851 0.01288 -0.0296 0.0618 1.0000
11.250 1.3314 0.02013 0.01448 -0.0279 0.0547 1.0000
11.500 1.3367 0.02172 0.01609 -0.0269 0.0494 1.0000
11.750 1.3406 0.02354 0.01792 -0.0261 0.0440 1.0000
12.000 1.3433 0.02553 0.01990 -0.0254 0.0386 1.0000
12.250 1.3485 0.02736 0.02175 -0.0248 0.0349 1.0000
12.500 1.3515 0.02938 0.02379 -0.0241 0.0313 1.0000
12.750 1.3553 0.03134 0.02577 -0.0235 0.0281 1.0000
13.000 1.3591 0.03333 0.02778 -0.0230 0.0258 1.0000
13.250 1.3604 0.03553 0.03001 -0.0224 0.0232 1.0000
13.500 1.3648 0.03750 0.03201 -0.0220 0.0214 1.0000
13.750 1.3670 0.03968 0.03421 -0.0216 0.0197 1.0000
14.000 1.3693 0.04184 0.03641 -0.0212 0.0178 1.0000
14.250 1.3721 0.04401 0.03863 -0.0209 0.0165 1.0000
14.500 1.3735 0.04642 0.04106 -0.0207 0.0151 1.0000
14.750 1.3770 0.04868 0.04337 -0.0205 0.0140 1.0000
15.000 1.3804 0.05102 0.04576 -0.0205 0.0130 1.0000
15.250 1.3824 0.05352 0.04830 -0.0205 0.0121 1.0000
15.500 1.3832 0.05624 0.05106 -0.0206 0.0109 1.0000
15.750 1.3871 0.05863 0.05352 -0.0207 0.0103 1.0000
16.000 1.3886 0.06136 0.05629 -0.0210 0.0096 1.0000
16.250 1.3864 0.06456 0.05953 -0.0213 0.0085 1.0000
16.500 1.3892 0.06723 0.06227 -0.0217 0.0080 1.0000
16.750 1.3908 0.07011 0.06520 -0.0221 0.0074 1.0000
17.000 1.3902 0.07329 0.06844 -0.0227 0.0070 1.0000
17.250 1.3847 0.07721 0.07242 -0.0235 0.0063 1.0000
17.500 1.3866 0.08022 0.07551 -0.0242 0.0061 1.0000
17.750 1.3854 0.08372 0.07910 -0.0251 0.0059 1.0000
18.000 1.3838 0.08732 0.08277 -0.0261 0.0055 1.0000
18.250 1.3826 0.09090 0.08641 -0.0272 0.0052 1.0000
18.500 1.3753 0.09552 0.09111 -0.0287 0.0049 1.0000
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