EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.67 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e625-il-1000000.txt Download as CSV file: xf-e625-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 625 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.3515 0.10471 0.10318 -0.0158 1.0000 0.0164
-11.250 -0.3539 0.09980 0.09828 -0.0177 1.0000 0.0164
-11.000 -0.3597 0.09400 0.09248 -0.0199 1.0000 0.0165
-10.750 -0.3734 0.08739 0.08589 -0.0219 1.0000 0.0168
-10.500 -0.3745 0.08344 0.08195 -0.0232 1.0000 0.0169
-10.250 -0.3806 0.07835 0.07688 -0.0251 1.0000 0.0169
-10.000 -0.3912 0.07234 0.07088 -0.0276 1.0000 0.0170
-9.750 -0.4026 0.06654 0.06510 -0.0306 1.0000 0.0171
-9.500 -0.4615 0.05308 0.05156 -0.0397 1.0000 0.0170
-9.250 -0.4919 0.04768 0.04608 -0.0391 1.0000 0.0170
-9.000 -0.5316 0.04135 0.03959 -0.0353 1.0000 0.0170
-8.750 -0.5126 0.03700 0.03501 -0.0394 0.9126 0.0172
-8.500 -0.5838 0.04334 0.04105 -0.0299 0.9550 0.0172
-8.250 -0.5497 0.04072 0.03817 -0.0342 0.9026 0.0176
-7.500 -0.5893 0.02355 0.01904 -0.0152 0.8134 0.0157
-7.250 -0.5764 0.02143 0.01657 -0.0125 0.7961 0.0154
-7.000 -0.5602 0.01940 0.01419 -0.0102 0.7795 0.0151
-6.750 -0.5396 0.01813 0.01267 -0.0087 0.7638 0.0151
-6.500 -0.5174 0.01697 0.01130 -0.0075 0.7491 0.0151
-6.250 -0.4939 0.01617 0.01034 -0.0065 0.7346 0.0153
-6.000 -0.4698 0.01555 0.00958 -0.0056 0.7210 0.0156
-5.750 -0.4452 0.01486 0.00874 -0.0048 0.7077 0.0158
-5.250 -0.3950 0.01379 0.00745 -0.0033 0.6815 0.0163
-5.000 -0.3697 0.01343 0.00700 -0.0026 0.6691 0.0164
-4.750 -0.3452 0.01265 0.00613 -0.0019 0.6565 0.0167
-4.500 -0.3221 0.01196 0.00538 -0.0008 0.6441 0.0171
-4.250 -0.2979 0.01156 0.00493 0.0000 0.6319 0.0173
-4.000 -0.2738 0.01124 0.00457 0.0009 0.6202 0.0177
-3.750 -0.2495 0.01096 0.00424 0.0018 0.6087 0.0180
-3.500 -0.2253 0.01069 0.00392 0.0027 0.5966 0.0184
-3.250 -0.2005 0.01046 0.00365 0.0035 0.5856 0.0189
-3.000 -0.1758 0.01027 0.00340 0.0043 0.5747 0.0194
-2.750 -0.1507 0.01013 0.00320 0.0050 0.5632 0.0201
-2.500 -0.1270 0.00982 0.00285 0.0060 0.5519 0.0213
-2.250 -0.1021 0.00966 0.00266 0.0068 0.5418 0.0222
-2.000 -0.0770 0.00954 0.00249 0.0075 0.5309 0.0235
-1.750 -0.0518 0.00941 0.00232 0.0082 0.5198 0.0251
-1.500 -0.0268 0.00929 0.00218 0.0090 0.5096 0.0291
-1.250 -0.0050 0.00894 0.00203 0.0103 0.4994 0.0822
-1.000 0.0181 0.00870 0.00195 0.0113 0.4897 0.1323
-0.750 0.0407 0.00849 0.00188 0.0124 0.4789 0.1912
-0.500 0.0584 0.00797 0.00178 0.0143 0.4694 0.3245
-0.250 0.0363 0.00610 0.00151 0.0246 0.4642 0.7726
0.000 0.0557 0.00597 0.00163 0.0269 0.4549 0.8564
0.250 0.0811 0.00606 0.00172 0.0278 0.4448 0.8812
0.500 0.1068 0.00618 0.00180 0.0285 0.4344 0.8966
0.750 0.1308 0.00631 0.00189 0.0297 0.4253 0.9089
1.000 0.1611 0.00651 0.00205 0.0295 0.4154 0.9180
1.250 0.1868 0.00667 0.00217 0.0303 0.4055 0.9265
1.500 0.2192 0.00687 0.00232 0.0295 0.3953 0.9311
1.750 0.2473 0.00707 0.00245 0.0297 0.3856 0.9363
2.000 0.2740 0.00723 0.00258 0.0302 0.3769 0.9418
2.250 0.3144 0.00754 0.00282 0.0277 0.3663 0.9444
2.500 0.3453 0.00766 0.00289 0.0271 0.3566 0.9458
2.750 0.3747 0.00776 0.00294 0.0267 0.3484 0.9472
3.000 0.4028 0.00788 0.00299 0.0266 0.3389 0.9488
3.250 0.4291 0.00796 0.00304 0.0269 0.3313 0.9509
3.500 0.4425 0.00800 0.00304 0.0300 0.3246 0.9554
3.750 0.4738 0.00809 0.00309 0.0292 0.3164 0.9563
4.000 0.5054 0.00822 0.00317 0.0283 0.3084 0.9571
4.250 0.5374 0.00833 0.00326 0.0273 0.3018 0.9578
4.500 0.5688 0.00848 0.00336 0.0264 0.2944 0.9585
4.750 0.6001 0.00861 0.00346 0.0256 0.2875 0.9592
5.000 0.6316 0.00874 0.00356 0.0246 0.2808 0.9599
5.250 0.6626 0.00890 0.00368 0.0238 0.2743 0.9607
5.500 0.6936 0.00901 0.00379 0.0229 0.2685 0.9615
5.750 0.7232 0.00920 0.00393 0.0224 0.2616 0.9627
6.000 0.7526 0.00932 0.00405 0.0219 0.2568 0.9640
6.250 0.7791 0.00946 0.00418 0.0220 0.2512 0.9661
6.750 0.8260 0.00972 0.00442 0.0235 0.2410 0.9708
7.000 0.8577 0.00988 0.00458 0.0224 0.2353 0.9713
7.250 0.8888 0.01009 0.00476 0.0213 0.2293 0.9719
7.500 0.9205 0.01023 0.00491 0.0203 0.2242 0.9725
7.750 0.9513 0.01045 0.00511 0.0193 0.2184 0.9733
8.000 0.9819 0.01064 0.00531 0.0184 0.2133 0.9741
8.250 1.0118 0.01082 0.00549 0.0176 0.2079 0.9752
8.500 1.0397 0.01110 0.00573 0.0172 0.2015 0.9765
8.750 1.0679 0.01125 0.00592 0.0168 0.1977 0.9780
9.000 1.0931 0.01147 0.00614 0.0169 0.1925 0.9801
9.250 1.1130 0.01176 0.00641 0.0182 0.1866 0.9831
9.500 1.1445 0.01194 0.00662 0.0170 0.1822 0.9837
9.750 1.1746 0.01223 0.00690 0.0159 0.1764 0.9844
10.000 1.2042 0.01250 0.00718 0.0150 0.1711 0.9853
10.250 1.2335 0.01276 0.00745 0.0142 0.1657 0.9862
10.500 1.2608 0.01315 0.00782 0.0136 0.1592 0.9875
10.750 1.2891 0.01340 0.00809 0.0129 0.1540 0.9889
11.000 1.3148 0.01382 0.00849 0.0126 0.1473 0.9907
11.250 1.3405 0.01414 0.00884 0.0124 0.1427 0.9926
11.500 1.3655 0.01455 0.00925 0.0121 0.1369 0.9942
11.750 1.3935 0.01497 0.00967 0.0112 0.1310 0.9952
12.000 1.4207 0.01539 0.01009 0.0104 0.1253 0.9965
12.250 1.4463 0.01591 0.01061 0.0098 0.1195 0.9980
12.500 1.4725 0.01636 0.01107 0.0091 0.1138 0.9993
12.750 1.4852 0.01688 0.01160 0.0110 0.1093 1.0000
13.000 1.4723 0.01715 0.01191 0.0181 0.1071 1.0000
13.250 1.4658 0.01750 0.01231 0.0237 0.1057 1.0000
13.500 1.4631 0.01803 0.01287 0.0282 0.1025 1.0000
13.750 1.4614 0.01882 0.01367 0.0320 0.0985 1.0000
14.000 1.4643 0.01966 0.01455 0.0348 0.0950 1.0000
14.250 1.4700 0.02053 0.01546 0.0368 0.0922 1.0000
14.500 1.4733 0.02170 0.01664 0.0388 0.0883 1.0000
14.750 1.4766 0.02304 0.01801 0.0403 0.0846 1.0000
15.000 1.4823 0.02434 0.01935 0.0415 0.0810 1.0000
15.250 1.4841 0.02606 0.02109 0.0425 0.0771 1.0000
15.500 1.4858 0.02791 0.02298 0.0432 0.0729 1.0000
15.750 1.4880 0.02984 0.02496 0.0437 0.0696 1.0000
16.000 1.4833 0.03248 0.02762 0.0441 0.0649 1.0000
16.250 1.4851 0.03463 0.02984 0.0443 0.0629 1.0000
16.500 1.4776 0.03774 0.03298 0.0442 0.0582 1.0000
16.750 1.4718 0.04082 0.03611 0.0440 0.0557 1.0000
17.000 1.4657 0.04398 0.03934 0.0436 0.0525 1.0000
17.250 1.4570 0.04757 0.04299 0.0430 0.0502 1.0000
17.500 1.4444 0.05173 0.04721 0.0421 0.0476 1.0000
17.750 1.4314 0.05608 0.05163 0.0410 0.0442 1.0000
18.000 1.4160 0.06084 0.05646 0.0396 0.0419 1.0000
18.250 1.3995 0.06586 0.06155 0.0381 0.0398 1.0000
18.500 1.3903 0.07006 0.06584 0.0368 0.0394 1.0000
18.750 1.3721 0.07551 0.07137 0.0349 0.0366 1.0000
19.000 1.3588 0.08040 0.07635 0.0332 0.0359 1.0000
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Polar data table (+)
Polar graphs
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