EPPLER 625 AIRFOIL (e625-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: EPPLER 625 AIRFOIL (e625-il) Reynolds number: 500,000 Max Cl/Cd: 82.89 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e625-il-500000.txt Download as CSV file: xf-e625-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4471 0.09917 0.09690 -0.0188 1.0000 0.0246
-10.500 -0.4429 0.09631 0.09407 -0.0193 1.0000 0.0248
-10.250 -0.4408 0.09296 0.09073 -0.0204 1.0000 0.0250
-10.000 -0.4400 0.08934 0.08713 -0.0220 1.0000 0.0252
-9.750 -0.4402 0.08563 0.08345 -0.0237 1.0000 0.0255
-9.500 -0.4442 0.08119 0.07905 -0.0266 1.0000 0.0259
-9.250 -0.4579 0.07527 0.07314 -0.0317 1.0000 0.0260
-9.000 -0.4796 0.06974 0.06757 -0.0340 1.0000 0.0258
-8.750 -0.4943 0.06647 0.06427 -0.0328 1.0000 0.0262
-8.500 -0.5118 0.06341 0.06116 -0.0298 1.0000 0.0263
-8.250 -0.5224 0.06011 0.05780 -0.0273 1.0000 0.0268
-8.000 -0.5688 0.05200 0.04903 -0.0199 0.9994 0.0292
-7.750 -0.5499 0.04614 0.04314 -0.0231 0.9685 0.0298
-7.500 -0.5130 0.04347 0.04039 -0.0276 0.9404 0.0303
-7.250 -0.4851 0.04139 0.03813 -0.0296 0.9035 0.0312
-7.000 -0.4745 0.03919 0.03565 -0.0274 0.8700 0.0321
-6.750 -0.4836 0.03457 0.03028 -0.0212 0.8445 0.0357
-6.500 -0.4673 0.03311 0.02874 -0.0197 0.8243 0.0362
-6.250 -0.4512 0.03186 0.02736 -0.0179 0.8060 0.0369
-6.000 -0.4351 0.03056 0.02589 -0.0160 0.7889 0.0381
-5.750 -0.4336 0.02049 0.01420 -0.0081 0.7780 0.0238
-5.500 -0.4096 0.01877 0.01225 -0.0072 0.7633 0.0234
-5.250 -0.3842 0.01753 0.01078 -0.0063 0.7491 0.0234
-5.000 -0.3582 0.01658 0.00965 -0.0057 0.7352 0.0235
-4.750 -0.3319 0.01577 0.00869 -0.0051 0.7219 0.0237
-4.500 -0.3059 0.01512 0.00791 -0.0045 0.7088 0.0240
-4.250 -0.2801 0.01455 0.00723 -0.0039 0.6954 0.0241
-4.000 -0.2548 0.01386 0.00647 -0.0032 0.6820 0.0245
-3.750 -0.2313 0.01316 0.00575 -0.0022 0.6695 0.0254
-3.500 -0.2077 0.01276 0.00530 -0.0012 0.6572 0.0262
-3.250 -0.1839 0.01245 0.00493 -0.0002 0.6448 0.0272
-3.000 -0.1603 0.01211 0.00454 0.0008 0.6326 0.0280
-2.750 -0.1363 0.01185 0.00421 0.0018 0.6209 0.0291
-2.500 -0.1138 0.01148 0.00379 0.0031 0.6094 0.0308
-2.250 -0.0897 0.01126 0.00354 0.0040 0.5977 0.0329
-2.000 -0.0657 0.01104 0.00328 0.0050 0.5863 0.0367
-1.750 -0.0430 0.01074 0.00304 0.0063 0.5752 0.0553
-1.500 -0.0233 0.01026 0.00288 0.0079 0.5640 0.1386
-1.250 -0.0026 0.00987 0.00275 0.0093 0.5534 0.2175
-1.000 0.0033 0.00878 0.00250 0.0134 0.5444 0.4634
-0.750 -0.0048 0.00740 0.00256 0.0214 0.5361 0.8299
-0.500 0.0252 0.00767 0.00286 0.0217 0.5249 0.8814
-0.250 0.0535 0.00806 0.00318 0.0225 0.5137 0.9053
0.000 0.0978 0.00863 0.00367 0.0199 0.5010 0.9181
0.250 0.1489 0.00929 0.00421 0.0158 0.4876 0.9273
0.500 0.2112 0.00985 0.00464 0.0092 0.4734 0.9296
0.750 0.2612 0.01029 0.00496 0.0050 0.4600 0.9337
1.000 0.2957 0.01066 0.00521 0.0040 0.4484 0.9415
1.250 0.3514 0.01100 0.00546 -0.0015 0.4349 0.9442
1.500 0.3825 0.01104 0.00542 -0.0022 0.4237 0.9457
1.750 0.4111 0.01109 0.00539 -0.0025 0.4133 0.9475
2.000 0.4379 0.01114 0.00538 -0.0023 0.4032 0.9499
2.250 0.4559 0.01119 0.00539 -0.0004 0.3945 0.9538
2.500 0.4788 0.01125 0.00537 0.0006 0.3851 0.9563
2.750 0.5121 0.01127 0.00535 -0.0007 0.3750 0.9572
3.000 0.5438 0.01133 0.00535 -0.0016 0.3656 0.9582
3.250 0.5742 0.01140 0.00536 -0.0023 0.3559 0.9594
3.500 0.6039 0.01146 0.00539 -0.0029 0.3474 0.9607
3.750 0.6327 0.01158 0.00544 -0.0032 0.3387 0.9625
4.000 0.6603 0.01165 0.00550 -0.0033 0.3308 0.9646
4.250 0.6830 0.01178 0.00558 -0.0024 0.3235 0.9673
4.500 0.7014 0.01188 0.00568 -0.0006 0.3174 0.9703
4.750 0.7338 0.01196 0.00572 -0.0018 0.3097 0.9711
5.000 0.7657 0.01205 0.00580 -0.0029 0.3024 0.9722
5.250 0.7964 0.01216 0.00588 -0.0037 0.2953 0.9734
5.500 0.8255 0.01230 0.00600 -0.0043 0.2891 0.9747
5.750 0.8541 0.01239 0.00610 -0.0047 0.2825 0.9763
6.000 0.8802 0.01260 0.00625 -0.0047 0.2759 0.9781
6.250 0.9062 0.01270 0.00639 -0.0045 0.2705 0.9802
6.500 0.9276 0.01290 0.00659 -0.0034 0.2648 0.9830
6.750 0.9586 0.01305 0.00672 -0.0045 0.2586 0.9839
7.000 0.9893 0.01314 0.00684 -0.0054 0.2525 0.9849
7.250 1.0181 0.01336 0.00703 -0.0060 0.2465 0.9862
7.500 1.0471 0.01349 0.00721 -0.0066 0.2410 0.9876
7.750 1.0749 0.01367 0.00739 -0.0070 0.2350 0.9892
8.000 1.1015 0.01395 0.00766 -0.0072 0.2295 0.9911
8.250 1.1288 0.01411 0.00787 -0.0075 0.2243 0.9929
8.500 1.1559 0.01436 0.00811 -0.0079 0.2182 0.9944
8.750 1.1849 0.01457 0.00836 -0.0086 0.2129 0.9956
9.000 1.2135 0.01477 0.00860 -0.0093 0.2073 0.9970
9.250 1.2399 0.01515 0.00894 -0.0097 0.2012 0.9985
9.500 1.2691 0.01531 0.00919 -0.0105 0.1961 0.9998
9.750 1.2880 0.01562 0.00952 -0.0092 0.1911 1.0000
10.000 1.3020 0.01603 0.00992 -0.0071 0.1864 1.0000
10.250 1.3186 0.01627 0.01024 -0.0054 0.1821 1.0000
10.500 1.3323 0.01661 0.01061 -0.0032 0.1775 1.0000
10.750 1.3417 0.01712 0.01109 -0.0004 0.1729 1.0000
11.000 1.3556 0.01736 0.01143 0.0018 0.1693 1.0000
11.250 1.3653 0.01772 0.01184 0.0047 0.1649 1.0000
11.500 1.3697 0.01820 0.01231 0.0083 0.1609 1.0000
11.750 1.3745 0.01859 0.01275 0.0120 0.1572 1.0000
12.000 1.3729 0.01887 0.01309 0.0170 0.1534 1.0000
12.250 1.3655 0.01926 0.01351 0.0227 0.1506 1.0000
12.500 1.3585 0.01989 0.01414 0.0279 0.1472 1.0000
12.750 1.3608 0.02048 0.01479 0.0313 0.1438 1.0000
13.000 1.3655 0.02114 0.01550 0.0340 0.1391 1.0000
13.250 1.3669 0.02212 0.01650 0.0367 0.1353 1.0000
13.500 1.3703 0.02319 0.01761 0.0388 0.1317 1.0000
13.750 1.3785 0.02411 0.01861 0.0402 0.1278 1.0000
14.000 1.3824 0.02542 0.01995 0.0417 0.1241 1.0000
14.250 1.3827 0.02713 0.02167 0.0430 0.1206 1.0000
14.500 1.3910 0.02835 0.02300 0.0438 0.1175 1.0000
14.750 1.3961 0.02991 0.02463 0.0445 0.1138 1.0000
15.000 1.3967 0.03192 0.02668 0.0451 0.1103 1.0000
15.250 1.3966 0.03411 0.02892 0.0455 0.1071 1.0000
15.500 1.4017 0.03591 0.03081 0.0457 0.1033 1.0000
15.750 1.4002 0.03839 0.03334 0.0458 0.0996 1.0000
16.000 1.3935 0.04148 0.03646 0.0456 0.0960 1.0000
16.250 1.3952 0.04377 0.03886 0.0455 0.0941 1.0000
16.500 1.3914 0.04673 0.04188 0.0451 0.0895 1.0000
16.750 1.3826 0.05036 0.04556 0.0444 0.0865 1.0000
17.000 1.3759 0.05383 0.04911 0.0437 0.0844 1.0000
17.250 1.3727 0.05700 0.05238 0.0429 0.0813 1.0000
17.500 1.3648 0.06082 0.05627 0.0419 0.0787 1.0000
17.750 1.3501 0.06559 0.06108 0.0404 0.0756 1.0000
18.000 1.3414 0.06967 0.06525 0.0391 0.0735 1.0000
18.250 1.3335 0.07373 0.06940 0.0378 0.0705 1.0000
18.500 1.3229 0.07819 0.07394 0.0363 0.0685 1.0000
18.750 1.3078 0.08340 0.07920 0.0343 0.0662 1.0000
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Polar data table (+)
Polar graphs
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