EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.2 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e625-il-1000000-n5.txt Download as CSV file: xf-e625-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.8404 0.04929 0.04711 -0.0471 1.0000 0.0086
-12.750 -0.9130 0.03951 0.03681 -0.0449 1.0000 0.0086
-12.500 -0.9307 0.03634 0.03342 -0.0413 1.0000 0.0086
-12.250 -0.9316 0.03474 0.03170 -0.0383 1.0000 0.0086
-12.000 -0.9318 0.03328 0.03012 -0.0351 1.0000 0.0087
-11.750 -0.9385 0.03137 0.02803 -0.0306 1.0000 0.0087
-11.500 -0.9383 0.03006 0.02659 -0.0266 1.0000 0.0088
-11.250 -0.9364 0.02848 0.02484 -0.0229 1.0000 0.0088
-11.000 -0.9279 0.02731 0.02355 -0.0201 1.0000 0.0089
-10.750 -0.9170 0.02630 0.02243 -0.0175 1.0000 0.0090
-10.250 -0.8615 0.02306 0.01880 -0.0198 0.9534 0.0091
-10.000 -0.8190 0.02158 0.01702 -0.0238 0.9025 0.0093
-9.750 -0.8031 0.02079 0.01596 -0.0217 0.8614 0.0094
-9.500 -0.7871 0.02002 0.01498 -0.0195 0.8344 0.0095
-9.250 -0.7693 0.01937 0.01415 -0.0177 0.8120 0.0096
-9.000 -0.7512 0.01855 0.01314 -0.0159 0.7926 0.0097
-8.750 -0.7311 0.01797 0.01241 -0.0144 0.7749 0.0098
-8.500 -0.7103 0.01740 0.01169 -0.0131 0.7589 0.0100
-8.250 -0.6886 0.01692 0.01109 -0.0119 0.7434 0.0101
-8.000 -0.6662 0.01647 0.01052 -0.0108 0.7289 0.0103
-7.750 -0.6435 0.01603 0.00996 -0.0097 0.7152 0.0104
-7.500 -0.6206 0.01557 0.00939 -0.0087 0.7015 0.0105
-7.250 -0.5984 0.01492 0.00863 -0.0076 0.6891 0.0106
-7.000 -0.5760 0.01432 0.00793 -0.0065 0.6762 0.0108
-6.750 -0.5527 0.01389 0.00742 -0.0055 0.6627 0.0109
-6.500 -0.5289 0.01351 0.00698 -0.0047 0.6505 0.0111
-6.250 -0.5047 0.01322 0.00662 -0.0039 0.6380 0.0113
-6.000 -0.4805 0.01290 0.00623 -0.0030 0.6263 0.0114
-5.750 -0.4560 0.01262 0.00589 -0.0022 0.6143 0.0116
-5.500 -0.4315 0.01232 0.00553 -0.0015 0.6031 0.0117
-5.250 -0.4069 0.01208 0.00523 -0.0007 0.5917 0.0120
-5.000 -0.3822 0.01183 0.00492 0.0001 0.5803 0.0122
-4.750 -0.3575 0.01158 0.00461 0.0008 0.5681 0.0124
-4.500 -0.3328 0.01136 0.00433 0.0016 0.5563 0.0127
-4.250 -0.3080 0.01115 0.00406 0.0023 0.5447 0.0129
-4.000 -0.2829 0.01098 0.00383 0.0030 0.5334 0.0131
-3.750 -0.2576 0.01081 0.00362 0.0037 0.5232 0.0133
-3.500 -0.2334 0.01056 0.00332 0.0045 0.5123 0.0138
-3.250 -0.2082 0.01040 0.00312 0.0052 0.5023 0.0143
-3.000 -0.1830 0.01026 0.00295 0.0059 0.4928 0.0148
-2.750 -0.1577 0.01014 0.00279 0.0065 0.4826 0.0154
-2.500 -0.1322 0.01003 0.00263 0.0072 0.4720 0.0160
-2.250 -0.1067 0.00993 0.00250 0.0078 0.4628 0.0164
-2.000 -0.0814 0.00982 0.00235 0.0084 0.4534 0.0173
-1.750 -0.0559 0.00973 0.00224 0.0090 0.4432 0.0184
-1.250 -0.0049 0.00958 0.00204 0.0102 0.4245 0.0242
-1.000 0.0192 0.00942 0.00195 0.0111 0.4156 0.0481
-0.750 0.0437 0.00929 0.00188 0.0118 0.4051 0.0734
-0.500 0.0681 0.00916 0.00183 0.0126 0.3968 0.1045
-0.250 0.0923 0.00904 0.00179 0.0134 0.3879 0.1424
0.000 0.1159 0.00888 0.00176 0.0142 0.3794 0.1925
0.250 0.1361 0.00855 0.00171 0.0157 0.3702 0.2944
0.500 0.1221 0.00684 0.00144 0.0241 0.3663 0.7194
0.750 0.1346 0.00650 0.00153 0.0278 0.3594 0.8424
1.000 0.1599 0.00656 0.00162 0.0286 0.3519 0.8692
1.250 0.1860 0.00664 0.00170 0.0292 0.3435 0.8864
1.500 0.2121 0.00675 0.00175 0.0297 0.3352 0.8957
1.750 0.2389 0.00685 0.00183 0.0301 0.3276 0.9038
2.000 0.2653 0.00696 0.00190 0.0305 0.3206 0.9116
2.250 0.2924 0.00709 0.00201 0.0309 0.3134 0.9196
2.500 0.3172 0.00720 0.00206 0.0316 0.3058 0.9233
2.750 0.3444 0.00727 0.00210 0.0317 0.2997 0.9251
3.000 0.3727 0.00739 0.00216 0.0316 0.2920 0.9267
3.250 0.4011 0.00748 0.00223 0.0315 0.2855 0.9283
3.500 0.4287 0.00759 0.00230 0.0315 0.2792 0.9301
3.750 0.4557 0.00770 0.00237 0.0316 0.2729 0.9319
4.000 0.4825 0.00780 0.00245 0.0318 0.2667 0.9339
4.250 0.5084 0.00793 0.00253 0.0322 0.2612 0.9360
4.500 0.5340 0.00802 0.00260 0.0326 0.2569 0.9383
4.750 0.5594 0.00812 0.00269 0.0331 0.2511 0.9405
5.000 0.5878 0.00828 0.00281 0.0328 0.2450 0.9420
5.250 0.6165 0.00838 0.00291 0.0325 0.2409 0.9435
5.500 0.6444 0.00852 0.00303 0.0324 0.2358 0.9451
5.750 0.6712 0.00868 0.00317 0.0324 0.2299 0.9470
6.000 0.6981 0.00880 0.00328 0.0325 0.2256 0.9491
6.250 0.7238 0.00894 0.00341 0.0328 0.2208 0.9516
6.500 0.7474 0.00910 0.00355 0.0335 0.2154 0.9543
6.750 0.7740 0.00923 0.00368 0.0336 0.2110 0.9562
7.000 0.8032 0.00942 0.00385 0.0331 0.2056 0.9574
7.250 0.8322 0.00962 0.00404 0.0325 0.2006 0.9588
7.500 0.8613 0.00979 0.00422 0.0320 0.1958 0.9603
7.750 0.8889 0.01001 0.00442 0.0317 0.1902 0.9621
8.000 0.9159 0.01021 0.00462 0.0316 0.1859 0.9641
8.250 0.9422 0.01039 0.00481 0.0316 0.1818 0.9663
8.500 0.9647 0.01061 0.00502 0.0324 0.1760 0.9693
8.750 0.9929 0.01085 0.00526 0.0319 0.1715 0.9706
9.000 1.0232 0.01108 0.00550 0.0310 0.1672 0.9715
9.250 1.0527 0.01138 0.00578 0.0301 0.1614 0.9725
9.500 1.0822 0.01164 0.00606 0.0292 0.1571 0.9734
9.750 1.1109 0.01192 0.00634 0.0285 0.1521 0.9745
10.000 1.1381 0.01227 0.00667 0.0281 0.1466 0.9758
10.250 1.1651 0.01254 0.00697 0.0277 0.1426 0.9774
10.500 1.1903 0.01286 0.00730 0.0276 0.1381 0.9794
10.750 1.2107 0.01324 0.00767 0.0285 0.1324 0.9825
11.000 1.2378 0.01360 0.00804 0.0279 0.1268 0.9836
11.250 1.2644 0.01407 0.00849 0.0273 0.1209 0.9848
11.500 1.2911 0.01449 0.00892 0.0267 0.1155 0.9861
11.750 1.3153 0.01503 0.00944 0.0264 0.1092 0.9879
12.000 1.3374 0.01550 0.00993 0.0265 0.1032 0.9903
12.250 1.3561 0.01603 0.01045 0.0273 0.0984 0.9932
12.500 1.3765 0.01662 0.01104 0.0275 0.0920 0.9956
12.750 1.3964 0.01735 0.01175 0.0274 0.0857 0.9980
13.250 1.4259 0.01873 0.01318 0.0292 0.0774 1.0000
13.500 1.4238 0.01958 0.01405 0.0328 0.0737 1.0000
13.750 1.4256 0.02053 0.01502 0.0356 0.0698 1.0000
14.000 1.4246 0.02185 0.01634 0.0380 0.0649 1.0000
14.250 1.4300 0.02297 0.01752 0.0396 0.0625 1.0000
14.500 1.4317 0.02451 0.01907 0.0411 0.0583 1.0000
14.750 1.4334 0.02620 0.02080 0.0422 0.0552 1.0000
15.000 1.4334 0.02818 0.02281 0.0430 0.0505 1.0000
15.250 1.4330 0.03034 0.02501 0.0436 0.0477 1.0000
15.500 1.4305 0.03280 0.02750 0.0439 0.0436 1.0000
15.750 1.4265 0.03553 0.03028 0.0440 0.0407 1.0000
16.000 1.4183 0.03879 0.03358 0.0439 0.0363 1.0000
16.250 1.4139 0.04177 0.03662 0.0437 0.0347 1.0000
16.500 1.3986 0.04601 0.04091 0.0430 0.0303 1.0000
16.750 1.3928 0.04938 0.04436 0.0424 0.0294 1.0000
17.000 1.3818 0.05346 0.04852 0.0414 0.0279 1.0000
17.250 1.3715 0.05757 0.05271 0.0403 0.0262 1.0000
17.500 1.3614 0.06177 0.05700 0.0391 0.0252 1.0000
17.750 1.3387 0.06768 0.06298 0.0372 0.0220 1.0000
18.000 1.3265 0.07238 0.06777 0.0357 0.0212 1.0000
18.250 1.3084 0.07795 0.07342 0.0338 0.0195 1.0000
18.500 1.3010 0.08212 0.07769 0.0323 0.0201 1.0000
18.750 1.2828 0.08793 0.08358 0.0302 0.0186 1.0000
19.000 1.2711 0.09286 0.08859 0.0283 0.0183 1.0000
19.250 1.2539 0.09867 0.09449 0.0260 0.0169 1.0000
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Polar data table (+)
Polar graphs
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