EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 500,000 Max Cl/Cd: 76.55 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e625-il-500000-n5.txt Download as CSV file: xf-e625-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4827 0.08250 0.08024 -0.0242 1.0000 0.0119
-10.000 -0.5102 0.07282 0.07057 -0.0324 1.0000 0.0117
-9.750 -0.5504 0.06419 0.06186 -0.0361 1.0000 0.0116
-9.500 -0.5886 0.05786 0.05540 -0.0339 1.0000 0.0116
-9.250 -0.6913 0.04040 0.03723 -0.0233 1.0000 0.0116
-9.000 -0.7012 0.02978 0.02551 -0.0225 0.9361 0.0117
-8.750 -0.6768 0.02701 0.02226 -0.0234 0.8947 0.0119
-8.500 -0.6629 0.02532 0.02018 -0.0212 0.8612 0.0121
-8.250 -0.6483 0.02395 0.01848 -0.0189 0.8370 0.0124
-8.000 -0.6321 0.02271 0.01691 -0.0168 0.8157 0.0127
-7.750 -0.6141 0.02155 0.01547 -0.0150 0.7975 0.0129
-7.500 -0.5944 0.02052 0.01417 -0.0134 0.7805 0.0130
-7.250 -0.5733 0.01967 0.01309 -0.0121 0.7646 0.0132
-7.000 -0.5512 0.01891 0.01213 -0.0109 0.7494 0.0133
-6.750 -0.5287 0.01798 0.01104 -0.0099 0.7357 0.0134
-6.500 -0.5058 0.01717 0.01012 -0.0089 0.7215 0.0137
-6.250 -0.4824 0.01662 0.00948 -0.0080 0.7081 0.0139
-6.000 -0.4587 0.01609 0.00884 -0.0072 0.6946 0.0141
-5.750 -0.4346 0.01561 0.00828 -0.0063 0.6811 0.0144
-5.500 -0.4105 0.01514 0.00772 -0.0055 0.6683 0.0146
-5.250 -0.3864 0.01473 0.00722 -0.0047 0.6562 0.0150
-5.000 -0.3624 0.01433 0.00673 -0.0038 0.6436 0.0153
-4.750 -0.3382 0.01394 0.00626 -0.0029 0.6315 0.0156
-4.500 -0.3138 0.01361 0.00586 -0.0021 0.6198 0.0161
-4.250 -0.2896 0.01332 0.00549 -0.0013 0.6082 0.0163
-4.000 -0.2661 0.01295 0.00506 -0.0003 0.5957 0.0169
-3.750 -0.2422 0.01263 0.00471 0.0006 0.5839 0.0175
-3.500 -0.2180 0.01238 0.00441 0.0015 0.5721 0.0180
-3.250 -0.1937 0.01217 0.00413 0.0023 0.5607 0.0185
-3.000 -0.1692 0.01196 0.00386 0.0031 0.5494 0.0192
-2.750 -0.1445 0.01179 0.00363 0.0039 0.5387 0.0200
-2.500 -0.1202 0.01160 0.00339 0.0047 0.5280 0.0210
-2.250 -0.0954 0.01144 0.00320 0.0055 0.5172 0.0224
-1.500 -0.0226 0.01095 0.00272 0.0080 0.4861 0.0504
-1.250 0.0009 0.01076 0.00261 0.0089 0.4769 0.0818
-1.000 0.0248 0.01061 0.00252 0.0098 0.4668 0.1108
-0.750 0.0480 0.01041 0.00245 0.0108 0.4568 0.1549
-0.500 0.0685 0.01008 0.00237 0.0121 0.4475 0.2390
-0.250 0.0648 0.00860 0.00209 0.0182 0.4406 0.5821
0.000 0.0698 0.00780 0.00227 0.0236 0.4331 0.8409
0.250 0.0962 0.00795 0.00243 0.0244 0.4231 0.8769
0.500 0.1250 0.00815 0.00258 0.0246 0.4132 0.8949
0.750 0.1534 0.00832 0.00269 0.0247 0.4036 0.9044
1.000 0.1821 0.00849 0.00280 0.0248 0.3943 0.9120
1.250 0.2130 0.00873 0.00295 0.0244 0.3841 0.9191
1.500 0.2437 0.00898 0.00315 0.0242 0.3752 0.9272
1.750 0.2793 0.00920 0.00330 0.0227 0.3661 0.9301
2.000 0.3076 0.00930 0.00333 0.0226 0.3570 0.9318
2.250 0.3344 0.00940 0.00336 0.0228 0.3486 0.9340
2.500 0.3577 0.00947 0.00338 0.0238 0.3409 0.9369
2.750 0.3765 0.00951 0.00338 0.0256 0.3343 0.9404
3.000 0.4071 0.00963 0.00344 0.0250 0.3259 0.9413
3.250 0.4377 0.00976 0.00352 0.0243 0.3183 0.9422
3.500 0.4680 0.00990 0.00361 0.0237 0.3102 0.9432
3.750 0.4976 0.01004 0.00371 0.0232 0.3034 0.9443
4.000 0.5267 0.01017 0.00380 0.0229 0.2961 0.9455
4.250 0.5549 0.01032 0.00391 0.0227 0.2896 0.9470
4.500 0.5827 0.01044 0.00401 0.0225 0.2829 0.9486
4.750 0.6083 0.01059 0.00412 0.0229 0.2766 0.9508
5.000 0.6238 0.01067 0.00420 0.0254 0.2723 0.9555
5.250 0.6546 0.01083 0.00433 0.0246 0.2656 0.9562
5.500 0.6850 0.01102 0.00450 0.0238 0.2596 0.9570
5.750 0.7158 0.01117 0.00465 0.0230 0.2542 0.9577
6.000 0.7458 0.01136 0.00481 0.0223 0.2483 0.9585
6.250 0.7756 0.01155 0.00501 0.0216 0.2430 0.9595
6.500 0.8053 0.01173 0.00519 0.0209 0.2372 0.9607
6.750 0.8336 0.01196 0.00539 0.0205 0.2320 0.9621
7.000 0.8610 0.01214 0.00560 0.0203 0.2270 0.9637
7.250 0.8864 0.01234 0.00579 0.0205 0.2214 0.9658
7.500 0.9029 0.01254 0.00598 0.0226 0.2169 0.9699
7.750 0.9335 0.01275 0.00623 0.0217 0.2122 0.9706
8.000 0.9634 0.01299 0.00647 0.0208 0.2064 0.9715
8.250 0.9922 0.01329 0.00676 0.0201 0.2008 0.9725
8.500 1.0211 0.01352 0.00702 0.0195 0.1961 0.9737
8.750 1.0485 0.01379 0.00731 0.0191 0.1908 0.9751
9.000 1.0746 0.01411 0.00763 0.0189 0.1857 0.9768
9.250 1.1000 0.01437 0.00793 0.0189 0.1808 0.9788
9.500 1.1222 0.01469 0.00826 0.0195 0.1760 0.9816
9.750 1.1471 0.01504 0.00863 0.0195 0.1714 0.9835
10.000 1.1754 0.01536 0.00899 0.0188 0.1662 0.9847
10.250 1.2018 0.01578 0.00942 0.0183 0.1610 0.9862
10.500 1.2278 0.01616 0.00984 0.0179 0.1565 0.9879
10.750 1.2526 0.01656 0.01028 0.0177 0.1514 0.9899
11.000 1.2748 0.01707 0.01080 0.0179 0.1467 0.9923
11.250 1.2987 0.01750 0.01129 0.0178 0.1426 0.9944
11.500 1.3239 0.01799 0.01182 0.0173 0.1375 0.9964
11.750 1.3457 0.01859 0.01243 0.0172 0.1324 0.9987
12.000 1.3612 0.01906 0.01295 0.0185 0.1273 1.0000
12.250 1.3546 0.01951 0.01343 0.0240 0.1245 1.0000
12.500 1.3495 0.02017 0.01411 0.0287 0.1211 1.0000
12.750 1.3510 0.02086 0.01484 0.0320 0.1177 1.0000
13.000 1.3524 0.02175 0.01576 0.0348 0.1121 1.0000
13.250 1.3533 0.02288 0.01690 0.0373 0.1084 1.0000
13.500 1.3589 0.02391 0.01799 0.0391 0.1048 1.0000
13.750 1.3625 0.02520 0.01932 0.0407 0.1003 1.0000
14.000 1.3645 0.02676 0.02091 0.0420 0.0969 1.0000
14.250 1.3695 0.02821 0.02243 0.0430 0.0940 1.0000
14.500 1.3734 0.02987 0.02415 0.0437 0.0907 1.0000
14.750 1.3736 0.03194 0.02626 0.0443 0.0868 1.0000
15.000 1.3742 0.03407 0.02845 0.0447 0.0835 1.0000
15.250 1.3757 0.03621 0.03067 0.0450 0.0809 1.0000
15.500 1.3724 0.03891 0.03341 0.0450 0.0770 1.0000
15.750 1.3673 0.04188 0.03644 0.0448 0.0737 1.0000
16.000 1.3618 0.04498 0.03960 0.0445 0.0689 1.0000
16.250 1.3597 0.04779 0.04251 0.0442 0.0683 1.0000
16.500 1.3462 0.05202 0.04677 0.0433 0.0635 1.0000
16.750 1.3393 0.05560 0.05044 0.0425 0.0608 1.0000
17.000 1.3323 0.05931 0.05423 0.0415 0.0592 1.0000
17.250 1.3182 0.06400 0.05898 0.0401 0.0563 1.0000
17.500 1.3083 0.06823 0.06331 0.0388 0.0547 1.0000
17.750 1.2946 0.07311 0.06825 0.0372 0.0511 1.0000
18.000 1.2824 0.07783 0.07306 0.0356 0.0493 1.0000
18.250 1.2647 0.08344 0.07873 0.0336 0.0465 1.0000
18.500 1.2559 0.08788 0.08326 0.0320 0.0457 1.0000
18.750 1.2426 0.09301 0.08847 0.0301 0.0434 1.0000
19.000 1.2311 0.09794 0.09349 0.0281 0.0424 1.0000
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