EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 500,000 Max Cl/Cd: 121.97 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e434-il-500000.txt Download as CSV file: xf-e434-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 434 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1045 0.08446 0.08194 -0.1019 0.9128 0.0158
-9.500 -0.1005 0.07893 0.07631 -0.1075 0.8898 0.0161
-9.250 -0.1003 0.07463 0.07193 -0.1102 0.8731 0.0162
-9.000 -0.1015 0.07045 0.06770 -0.1127 0.8599 0.0162
-8.750 -0.1058 0.06592 0.06311 -0.1154 0.8488 0.0163
-8.500 -0.1073 0.06358 0.06076 -0.1152 0.8395 0.0165
-8.250 -0.1210 0.05841 0.05552 -0.1190 0.8295 0.0165
-8.000 -0.1307 0.05585 0.05289 -0.1181 0.8216 0.0166
-7.750 -0.1336 0.05296 0.04992 -0.1180 0.8149 0.0167
-7.500 -0.1319 0.05071 0.04761 -0.1176 0.8088 0.0169
-7.250 -0.1293 0.04790 0.04466 -0.1173 0.8035 0.0172
-7.000 -0.1246 0.04501 0.04166 -0.1169 0.7981 0.0175
-6.750 -0.1181 0.04198 0.03848 -0.1162 0.7932 0.0181
-6.500 -0.1152 0.03712 0.03294 -0.1138 0.7886 0.0201
-6.250 -0.1074 0.03325 0.02900 -0.1130 0.7843 0.0206
-4.750 0.0026 0.01871 0.01271 -0.1059 0.7615 0.0174
-4.500 0.0279 0.01490 0.00816 -0.1036 0.7585 0.0103
-4.250 0.0537 0.01411 0.00722 -0.1032 0.7552 0.0102
-4.000 0.0779 0.01315 0.00622 -0.1025 0.7515 0.0104
-3.750 0.1029 0.01251 0.00554 -0.1020 0.7479 0.0107
-3.500 0.1285 0.01201 0.00500 -0.1017 0.7446 0.0115
-3.250 0.1550 0.01167 0.00456 -0.1014 0.7415 0.0128
-3.000 0.1802 0.01121 0.00411 -0.1010 0.7380 0.0148
-2.750 0.2064 0.01087 0.00375 -0.1007 0.7344 0.0193
-2.500 0.2311 0.01023 0.00337 -0.1003 0.7309 0.0735
-2.250 0.2564 0.00975 0.00321 -0.1002 0.7277 0.1689
-2.000 0.2795 0.00902 0.00310 -0.1000 0.7244 0.3561
-1.750 0.2950 0.00775 0.00315 -0.0981 0.7206 0.7253
-1.500 0.3190 0.00780 0.00332 -0.0968 0.7170 0.8053
-1.250 0.3451 0.00790 0.00337 -0.0962 0.7136 0.8291
-1.000 0.3713 0.00806 0.00345 -0.0956 0.7104 0.8463
-0.750 0.3960 0.00815 0.00354 -0.0947 0.7067 0.8603
-0.500 0.4212 0.00824 0.00361 -0.0939 0.7027 0.8726
-0.250 0.4455 0.00832 0.00365 -0.0929 0.6990 0.8815
0.000 0.4712 0.00842 0.00367 -0.0923 0.6957 0.8900
0.250 0.4932 0.00852 0.00378 -0.0907 0.6917 0.9017
0.500 0.5102 0.00861 0.00389 -0.0878 0.6874 0.9167
0.750 0.5277 0.00863 0.00390 -0.0850 0.6835 0.9286
1.000 0.5525 0.00866 0.00386 -0.0843 0.6798 0.9346
1.250 0.5770 0.00862 0.00383 -0.0837 0.6752 0.9381
1.500 0.6035 0.00860 0.00379 -0.0835 0.6705 0.9414
1.750 0.6309 0.00860 0.00373 -0.0836 0.6664 0.9444
2.000 0.6578 0.00860 0.00371 -0.0836 0.6619 0.9470
2.250 0.6837 0.00856 0.00369 -0.0833 0.6567 0.9498
2.500 0.7107 0.00854 0.00364 -0.0833 0.6520 0.9526
2.750 0.7377 0.00856 0.00364 -0.0833 0.6472 0.9555
3.000 0.7630 0.00854 0.00364 -0.0830 0.6414 0.9590
3.250 0.7906 0.00853 0.00361 -0.0831 0.6361 0.9618
3.500 0.8182 0.00854 0.00363 -0.0833 0.6303 0.9648
3.750 0.8452 0.00854 0.00364 -0.0833 0.6238 0.9683
4.000 0.8723 0.00857 0.00364 -0.0834 0.6177 0.9718
4.250 0.9019 0.00858 0.00371 -0.0840 0.6102 0.9746
4.500 0.9327 0.00865 0.00374 -0.0850 0.6034 0.9772
4.750 0.9627 0.00868 0.00382 -0.0857 0.5949 0.9808
5.000 0.9932 0.00876 0.00390 -0.0866 0.5868 0.9842
5.250 1.0263 0.00885 0.00400 -0.0881 0.5771 0.9865
5.500 1.0585 0.00895 0.00412 -0.0895 0.5664 0.9893
5.750 1.0899 0.00907 0.00425 -0.0906 0.5552 0.9928
6.000 1.1215 0.00923 0.00440 -0.0919 0.5428 0.9967
6.250 1.1441 0.00938 0.00455 -0.0913 0.5298 1.0000
6.500 1.1577 0.00953 0.00469 -0.0889 0.5162 1.0000
6.750 1.1771 0.00974 0.00488 -0.0877 0.5004 1.0000
7.000 1.1971 0.01001 0.00512 -0.0866 0.4825 1.0000
7.250 1.2167 0.01032 0.00539 -0.0855 0.4626 1.0000
7.500 1.2338 0.01071 0.00571 -0.0839 0.4413 1.0000
7.750 1.2486 0.01112 0.00606 -0.0819 0.4204 1.0000
8.000 1.2606 0.01160 0.00646 -0.0794 0.3978 1.0000
8.250 1.2715 0.01216 0.00694 -0.0768 0.3755 1.0000
8.500 1.2821 0.01275 0.00746 -0.0742 0.3532 1.0000
8.750 1.2910 0.01344 0.00807 -0.0714 0.3309 1.0000
9.000 1.2993 0.01420 0.00874 -0.0687 0.3078 1.0000
9.250 1.3068 0.01504 0.00950 -0.0660 0.2865 1.0000
9.500 1.3152 0.01589 0.01029 -0.0636 0.2662 1.0000
9.750 1.3222 0.01686 0.01119 -0.0611 0.2467 1.0000
10.000 1.3290 0.01790 0.01216 -0.0588 0.2272 1.0000
10.250 1.3358 0.01901 0.01320 -0.0566 0.2078 1.0000
10.500 1.3424 0.02018 0.01432 -0.0545 0.1903 1.0000
10.750 1.3479 0.02147 0.01554 -0.0524 0.1733 1.0000
11.000 1.3547 0.02274 0.01677 -0.0506 0.1580 1.0000
11.250 1.3611 0.02408 0.01806 -0.0489 0.1428 1.0000
11.500 1.3673 0.02548 0.01943 -0.0472 0.1288 1.0000
11.750 1.3731 0.02694 0.02086 -0.0456 0.1158 1.0000
12.000 1.3784 0.02849 0.02239 -0.0440 0.1035 1.0000
12.250 1.3831 0.03012 0.02399 -0.0425 0.0919 1.0000
12.500 1.3875 0.03183 0.02567 -0.0411 0.0812 1.0000
12.750 1.3924 0.03355 0.02738 -0.0399 0.0716 1.0000
13.000 1.3969 0.03535 0.02919 -0.0387 0.0630 1.0000
13.250 1.4009 0.03726 0.03110 -0.0375 0.0555 1.0000
13.500 1.4032 0.03937 0.03321 -0.0364 0.0487 1.0000
13.750 1.4066 0.04144 0.03530 -0.0355 0.0429 1.0000
14.000 1.4101 0.04358 0.03749 -0.0347 0.0382 1.0000
14.250 1.4105 0.04609 0.04001 -0.0339 0.0341 1.0000
14.500 1.4147 0.04828 0.04228 -0.0333 0.0308 1.0000
14.750 1.4144 0.05102 0.04504 -0.0328 0.0278 1.0000
15.000 1.4175 0.05346 0.04757 -0.0324 0.0253 1.0000
15.250 1.4185 0.05619 0.05035 -0.0322 0.0231 1.0000
15.500 1.4182 0.05916 0.05339 -0.0320 0.0211 1.0000
15.750 1.4205 0.06189 0.05622 -0.0321 0.0194 1.0000
16.000 1.4159 0.06555 0.05992 -0.0322 0.0176 1.0000
16.250 1.4191 0.06833 0.06282 -0.0325 0.0163 1.0000
16.500 1.4196 0.07149 0.06604 -0.0329 0.0149 1.0000
16.750 1.4136 0.07564 0.07027 -0.0335 0.0138 1.0000
17.000 1.4150 0.07885 0.07360 -0.0341 0.0127 1.0000
17.250 1.4126 0.08267 0.07752 -0.0350 0.0118 1.0000
17.500 1.4029 0.08765 0.08258 -0.0363 0.0110 1.0000
17.750 1.4014 0.09151 0.08658 -0.0374 0.0102 1.0000
18.000 1.3994 0.09550 0.09066 -0.0386 0.0093 1.0000
18.250 1.3904 0.10072 0.09598 -0.0404 0.0088 1.0000
18.500 1.3826 0.10584 0.10121 -0.0423 0.0082 1.0000
18.750 1.3777 0.11054 0.10605 -0.0442 0.0076 1.0000
19.000 1.3727 0.11532 0.11094 -0.0462 0.0069 1.0000
19.250 1.3614 0.12131 0.11702 -0.0489 0.0065 1.0000
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