EPPLER 340 AIRFOIL (e340-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 340 AIRFOIL (e340-il) Reynolds number: 500,000 Max Cl/Cd: 80.32 at α=10.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e340-il-500000.txt Download as CSV file: xf-e340-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 340 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5505 0.08509 0.08316 -0.0040 1.0000 0.0160
-9.250 -0.5662 0.07853 0.07655 -0.0087 1.0000 0.0160
-9.000 -0.5823 0.07344 0.07140 -0.0101 1.0000 0.0161
-8.750 -0.5977 0.06905 0.06692 -0.0096 1.0000 0.0163
-8.500 -0.6119 0.06465 0.06241 -0.0077 1.0000 0.0167
-8.250 -0.6413 0.05528 0.05255 -0.0035 1.0000 0.0176
-8.000 -0.6403 0.05327 0.05022 -0.0006 0.8420 0.0178
-7.750 -0.6355 0.05152 0.04823 0.0016 0.7946 0.0180
-7.500 -0.6280 0.04961 0.04610 0.0035 0.7626 0.0183
-7.250 -0.6194 0.04730 0.04356 0.0054 0.7376 0.0188
-7.000 -0.6099 0.04453 0.04053 0.0076 0.7168 0.0197
-6.750 -0.6091 0.03895 0.03428 0.0124 0.7028 0.0217
-6.500 -0.5930 0.03722 0.03244 0.0136 0.6846 0.0220
-6.250 -0.5766 0.03555 0.03059 0.0150 0.6678 0.0226
-6.000 -0.5593 0.03372 0.02852 0.0167 0.6524 0.0240
-5.750 -0.5455 0.03091 0.02524 0.0195 0.6391 0.0265
-5.500 -0.5246 0.02964 0.02386 0.0204 0.6243 0.0275
-5.250 -0.5076 0.02792 0.02161 0.0230 0.6115 0.0313
-5.000 -0.4740 0.01960 0.01219 0.0260 0.6026 0.0144
-4.750 -0.4455 0.01851 0.01096 0.0261 0.5898 0.0139
-4.500 -0.4163 0.01711 0.00943 0.0261 0.5774 0.0136
-4.250 -0.3883 0.01607 0.00827 0.0264 0.5659 0.0134
-4.000 -0.3618 0.01526 0.00734 0.0268 0.5548 0.0134
-3.750 -0.3364 0.01459 0.00658 0.0275 0.5435 0.0135
-3.500 -0.3118 0.01403 0.00594 0.0283 0.5333 0.0138
-3.250 -0.2879 0.01352 0.00534 0.0292 0.5237 0.0143
-3.000 -0.2643 0.01298 0.00480 0.0301 0.5145 0.0156
-2.500 -0.2154 0.01227 0.00398 0.0317 0.4971 0.0217
-2.250 -0.1929 0.01176 0.00359 0.0328 0.4891 0.0528
-2.000 -0.1726 0.01107 0.00335 0.0341 0.4813 0.1546
-1.750 -0.1710 0.00939 0.00292 0.0386 0.4754 0.4765
-1.500 -0.1602 0.00854 0.00364 0.0432 0.4694 0.8495
-1.250 -0.1500 0.00900 0.00404 0.0477 0.4631 0.8842
-1.000 -0.0865 0.01101 0.00591 0.0427 0.4542 0.9028
-0.750 -0.0586 0.01155 0.00638 0.0434 0.4474 0.9136
-0.500 0.0167 0.01249 0.00712 0.0348 0.4381 0.9171
-0.250 0.0481 0.01304 0.00761 0.0347 0.4320 0.9282
0.000 0.1032 0.01330 0.00772 0.0296 0.4249 0.9309
0.250 0.1399 0.01333 0.00768 0.0278 0.4191 0.9331
0.500 0.1716 0.01332 0.00761 0.0269 0.4135 0.9354
0.750 0.1966 0.01338 0.00759 0.0274 0.4089 0.9393
1.000 0.2215 0.01341 0.00755 0.0278 0.4046 0.9426
1.250 0.2563 0.01332 0.00744 0.0263 0.3999 0.9437
1.500 0.2898 0.01329 0.00734 0.0250 0.3952 0.9450
1.750 0.3219 0.01333 0.00729 0.0239 0.3905 0.9467
2.000 0.3517 0.01329 0.00726 0.0234 0.3865 0.9488
2.250 0.3754 0.01333 0.00728 0.0241 0.3824 0.9520
2.500 0.4012 0.01334 0.00725 0.0243 0.3784 0.9544
2.750 0.4342 0.01335 0.00718 0.0230 0.3742 0.9552
3.000 0.4671 0.01329 0.00714 0.0218 0.3709 0.9564
3.250 0.4983 0.01326 0.00711 0.0209 0.3672 0.9578
3.500 0.5272 0.01326 0.00709 0.0205 0.3635 0.9593
3.750 0.5540 0.01334 0.00712 0.0204 0.3597 0.9613
4.000 0.5736 0.01348 0.00727 0.0219 0.3565 0.9640
4.250 0.6057 0.01339 0.00721 0.0208 0.3528 0.9647
4.500 0.6376 0.01334 0.00717 0.0197 0.3490 0.9655
4.750 0.6690 0.01336 0.00718 0.0187 0.3455 0.9666
5.000 0.6984 0.01348 0.00725 0.0180 0.3417 0.9678
5.250 0.7261 0.01346 0.00730 0.0178 0.3385 0.9688
5.500 0.7530 0.01349 0.00736 0.0177 0.3348 0.9702
5.750 0.7769 0.01357 0.00746 0.0182 0.3312 0.9718
6.000 0.7989 0.01373 0.00758 0.0191 0.3273 0.9730
6.250 0.8288 0.01372 0.00764 0.0184 0.3237 0.9735
6.500 0.8594 0.01370 0.00768 0.0175 0.3197 0.9743
6.750 0.8894 0.01372 0.00772 0.0167 0.3155 0.9752
7.000 0.9168 0.01388 0.00785 0.0164 0.3109 0.9759
7.250 0.9432 0.01388 0.00795 0.0163 0.3069 0.9766
7.500 0.9690 0.01392 0.00805 0.0164 0.3025 0.9772
7.750 0.9943 0.01402 0.00817 0.0165 0.2982 0.9780
8.000 1.0192 0.01417 0.00835 0.0167 0.2935 0.9791
8.250 1.0426 0.01422 0.00848 0.0173 0.2883 0.9798
8.500 1.0645 0.01434 0.00863 0.0181 0.2833 0.9803
8.750 1.0850 0.01452 0.00885 0.0192 0.2784 0.9810
9.000 1.1133 0.01454 0.00896 0.0186 0.2719 0.9815
9.250 1.1408 0.01471 0.00912 0.0181 0.2651 0.9821
9.500 1.1671 0.01477 0.00930 0.0180 0.2585 0.9827
9.750 1.1902 0.01499 0.00951 0.0184 0.2510 0.9831
10.000 1.2139 0.01513 0.00975 0.0187 0.2429 0.9836
10.250 1.2355 0.01540 0.01003 0.0193 0.2349 0.9841
10.500 1.2570 0.01565 0.01033 0.0199 0.2251 0.9846
10.750 1.2779 0.01598 0.01069 0.0206 0.2139 0.9855
11.000 1.2964 0.01640 0.01112 0.0216 0.2021 0.9865
11.250 1.3110 0.01690 0.01162 0.0233 0.1898 0.9872
11.500 1.3222 0.01748 0.01219 0.0256 0.1774 0.9882
11.750 1.3398 0.01813 0.01282 0.0263 0.1630 0.9888
12.000 1.3546 0.01888 0.01356 0.0274 0.1488 0.9897
12.250 1.3660 0.01973 0.01441 0.0289 0.1357 0.9908
12.500 1.3753 0.02071 0.01537 0.0306 0.1236 0.9927
12.750 1.3755 0.02171 0.01638 0.0338 0.1142 0.9945
13.000 1.3760 0.02271 0.01744 0.0363 0.1059 0.9962
13.250 1.3739 0.02435 0.01912 0.0377 0.0984 0.9981
13.500 1.3716 0.02663 0.02145 0.0378 0.0910 1.0000
13.750 1.3530 0.02895 0.02384 0.0408 0.0876 1.0000
14.000 1.3364 0.03138 0.02635 0.0434 0.0840 1.0000
14.250 1.3158 0.03420 0.02923 0.0459 0.0809 1.0000
14.500 1.2924 0.03726 0.03234 0.0485 0.0785 1.0000
14.750 1.2711 0.04012 0.03527 0.0510 0.0762 1.0000
15.000 1.2509 0.04307 0.03829 0.0530 0.0737 1.0000
15.250 1.2327 0.04663 0.04191 0.0537 0.0708 1.0000
15.500 1.2153 0.05087 0.04619 0.0531 0.0676 1.0000
15.750 1.2057 0.05455 0.04995 0.0523 0.0642 1.0000
16.000 1.1930 0.05886 0.05431 0.0510 0.0607 1.0000
16.500 1.1722 0.06735 0.06290 0.0482 0.0543 1.0000
16.750 1.1610 0.07185 0.06745 0.0466 0.0512 1.0000
17.000 1.1495 0.07645 0.07209 0.0449 0.0486 1.0000
17.250 1.1435 0.08042 0.07612 0.0434 0.0456 1.0000
17.500 1.1329 0.08506 0.08080 0.0417 0.0430 1.0000
17.750 1.1241 0.08949 0.08527 0.0400 0.0405 1.0000
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