EPPLER 68 AIRFOIL (e68-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: EPPLER 68 AIRFOIL (e68-il) Reynolds number: 200,000 Max Cl/Cd: 82.19 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e68-il-200000.txt Download as CSV file: xf-e68-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 68 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4338 0.09856 0.09537 -0.0398 1.0000 0.0645
-9.250 -0.4451 0.09602 0.09289 -0.0386 1.0000 0.0652
-9.000 -0.5775 0.06158 0.05825 -0.0669 0.9905 0.0372
-8.750 -0.5845 0.05349 0.04982 -0.0742 0.9828 0.0354
-8.500 -0.6074 0.04086 0.03572 -0.0789 0.9719 0.0307
-8.250 -0.5929 0.03809 0.03256 -0.0788 0.9654 0.0305
-8.000 -0.5703 0.03462 0.02864 -0.0803 0.9612 0.0305
-7.750 -0.5437 0.03084 0.02452 -0.0825 0.9588 0.0316
-7.500 -0.5246 0.02936 0.02291 -0.0819 0.9525 0.0328
-7.250 -0.4952 0.02772 0.02105 -0.0830 0.9487 0.0340
-7.000 -0.4614 0.02595 0.01900 -0.0847 0.9462 0.0350
-6.750 -0.4327 0.02456 0.01742 -0.0852 0.9423 0.0364
-6.500 -0.4079 0.02346 0.01616 -0.0849 0.9367 0.0378
-6.250 -0.3760 0.02189 0.01451 -0.0862 0.9336 0.0406
-6.000 -0.3392 0.02102 0.01362 -0.0883 0.9315 0.0465
-5.750 -0.3185 0.02010 0.01269 -0.0874 0.9250 0.0539
-5.500 -0.2879 0.01904 0.01166 -0.0883 0.9208 0.0747
-5.250 -0.2514 0.01826 0.01097 -0.0905 0.9183 0.1033
-5.000 -0.2123 0.01765 0.01046 -0.0931 0.9164 0.1340
-4.750 -0.1945 0.01740 0.01029 -0.0916 0.9083 0.1618
-4.500 -0.1587 0.01687 0.00989 -0.0935 0.9052 0.2031
-4.250 -0.1201 0.01629 0.00946 -0.0959 0.9031 0.2482
-4.000 -0.0797 0.01574 0.00906 -0.0987 0.9016 0.2996
-3.750 -0.0636 0.01561 0.00903 -0.0966 0.8927 0.3378
-3.500 -0.0259 0.01517 0.00876 -0.0987 0.8902 0.3923
-3.250 0.0146 0.01476 0.00847 -0.1012 0.8885 0.4465
-3.000 0.0548 0.01439 0.00822 -0.1035 0.8869 0.4955
-2.750 0.0719 0.01440 0.00830 -0.1014 0.8779 0.5292
-2.500 0.1087 0.01411 0.00807 -0.1030 0.8751 0.5683
-2.250 0.1472 0.01380 0.00783 -0.1048 0.8730 0.6052
-2.000 0.1681 0.01381 0.00790 -0.1033 0.8652 0.6343
-1.750 0.2016 0.01359 0.00773 -0.1040 0.8613 0.6654
-1.500 0.2382 0.01334 0.00751 -0.1053 0.8587 0.6956
-1.250 0.2603 0.01336 0.00758 -0.1039 0.8512 0.7215
-1.000 0.2916 0.01319 0.00744 -0.1042 0.8465 0.7485
-0.750 0.3265 0.01296 0.00724 -0.1050 0.8434 0.7726
-0.500 0.3455 0.01303 0.00735 -0.1029 0.8349 0.7960
-0.250 0.3762 0.01284 0.00718 -0.1029 0.8304 0.8182
0.000 0.4008 0.01279 0.00715 -0.1018 0.8243 0.8410
0.250 0.4236 0.01272 0.00711 -0.1001 0.8174 0.8621
0.500 0.4544 0.01252 0.00688 -0.1000 0.8134 0.8842
0.750 0.4690 0.01254 0.00695 -0.0968 0.8041 0.9069
1.000 0.5003 0.01233 0.00672 -0.0969 0.7995 0.9290
1.250 0.5301 0.01231 0.00672 -0.0970 0.7911 0.9498
1.500 0.5772 0.01215 0.00651 -0.1007 0.7858 0.9651
1.750 0.6241 0.01209 0.00645 -0.1046 0.7782 0.9787
2.000 0.6766 0.01194 0.00626 -0.1097 0.7713 0.9882
2.250 0.7253 0.01187 0.00619 -0.1142 0.7625 1.0000
2.500 0.7482 0.01177 0.00603 -0.1134 0.7547 1.0000
2.750 0.7579 0.01184 0.00610 -0.1102 0.7438 1.0000
3.000 0.7783 0.01188 0.00610 -0.1088 0.7342 1.0000
3.250 0.8065 0.01185 0.00602 -0.1089 0.7254 1.0000
3.500 0.8276 0.01193 0.00611 -0.1076 0.7139 1.0000
3.750 0.8520 0.01200 0.00616 -0.1069 0.7029 1.0000
4.000 0.8787 0.01205 0.00618 -0.1066 0.6923 1.0000
4.250 0.9057 0.01210 0.00620 -0.1064 0.6811 1.0000
4.500 0.9288 0.01220 0.00632 -0.1054 0.6682 1.0000
4.750 0.9526 0.01230 0.00643 -0.1045 0.6548 1.0000
5.000 0.9763 0.01241 0.00654 -0.1037 0.6410 1.0000
5.250 0.9998 0.01254 0.00667 -0.1027 0.6265 1.0000
5.500 1.0228 0.01268 0.00681 -0.1017 0.6112 1.0000
5.750 1.0453 0.01283 0.00695 -0.1006 0.5948 1.0000
6.000 1.0675 0.01302 0.00710 -0.0994 0.5778 1.0000
6.250 1.0874 0.01323 0.00734 -0.0978 0.5590 1.0000
6.500 1.1067 0.01347 0.00757 -0.0962 0.5388 1.0000
6.750 1.1256 0.01375 0.00780 -0.0944 0.5180 1.0000
7.000 1.1418 0.01406 0.00809 -0.0922 0.4941 1.0000
7.250 1.1570 0.01442 0.00841 -0.0898 0.4691 1.0000
7.500 1.1704 0.01486 0.00878 -0.0872 0.4426 1.0000
7.750 1.1811 0.01534 0.00918 -0.0841 0.4149 1.0000
8.000 1.1897 0.01588 0.00964 -0.0807 0.3864 1.0000
8.250 1.1970 0.01654 0.01019 -0.0772 0.3564 1.0000
8.500 1.2028 0.01731 0.01083 -0.0736 0.3240 1.0000
8.750 1.2072 0.01822 0.01158 -0.0700 0.2896 1.0000
9.000 1.2103 0.01927 0.01245 -0.0664 0.2555 1.0000
9.250 1.2136 0.02041 0.01343 -0.0631 0.2232 1.0000
9.500 1.2180 0.02159 0.01447 -0.0602 0.1934 1.0000
9.750 1.2230 0.02283 0.01559 -0.0574 0.1682 1.0000
10.000 1.2291 0.02408 0.01675 -0.0550 0.1452 1.0000
10.250 1.2333 0.02550 0.01807 -0.0525 0.1254 1.0000
10.500 1.2391 0.02689 0.01941 -0.0503 0.1063 1.0000
10.750 1.2423 0.02853 0.02096 -0.0479 0.0889 1.0000
11.000 1.2437 0.03037 0.02272 -0.0456 0.0740 1.0000
11.250 1.2445 0.03236 0.02471 -0.0433 0.0599 1.0000
11.500 1.2417 0.03473 0.02705 -0.0410 0.0499 1.0000
11.750 1.2418 0.03696 0.02930 -0.0390 0.0435 1.0000
12.000 1.2408 0.03938 0.03179 -0.0372 0.0393 1.0000
12.250 1.2445 0.04145 0.03394 -0.0358 0.0361 1.0000
12.500 1.2444 0.04394 0.03644 -0.0344 0.0338 1.0000
12.750 1.2464 0.04639 0.03896 -0.0331 0.0318 1.0000
13.000 1.2525 0.04849 0.04119 -0.0321 0.0302 1.0000
13.250 1.2585 0.05066 0.04347 -0.0311 0.0289 1.0000
13.500 1.2645 0.05288 0.04575 -0.0303 0.0277 1.0000
13.750 1.2714 0.05511 0.04806 -0.0295 0.0268 1.0000
14.000 1.2839 0.05750 0.05046 -0.0283 0.0255 1.0000
14.250 1.2904 0.05996 0.05311 -0.0277 0.0249 1.0000
14.500 1.2941 0.06259 0.05594 -0.0272 0.0242 1.0000
14.750 1.2968 0.06543 0.05897 -0.0269 0.0234 1.0000
15.000 1.2988 0.06842 0.06215 -0.0267 0.0227 1.0000
15.250 1.3000 0.07174 0.06567 -0.0265 0.0224 1.0000
15.500 1.2987 0.07534 0.06947 -0.0266 0.0220 1.0000
15.750 1.2951 0.07933 0.07366 -0.0269 0.0217 1.0000
16.000 1.2889 0.08371 0.07825 -0.0276 0.0215 1.0000
16.250 1.2804 0.08852 0.08329 -0.0287 0.0213 1.0000
16.500 1.2694 0.09384 0.08883 -0.0303 0.0213 1.0000
16.750 1.2560 0.09972 0.09495 -0.0324 0.0212 1.0000
17.000 1.2397 0.10629 0.10176 -0.0352 0.0213 1.0000
17.250 1.2168 0.11439 0.11015 -0.0393 0.0215 1.0000
17.500 1.1907 0.12359 0.11963 -0.0446 0.0217 1.0000
17.750 1.1611 0.13426 0.13057 -0.0513 0.0221 1.0000
18.000 1.1261 0.14724 0.14381 -0.0600 0.0227 1.0000
18.250 1.0817 0.16434 0.16112 -0.0717 0.0236 1.0000
18.500 1.0387 0.18344 0.18028 -0.0835 0.0249 1.0000
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Polar data table (+)
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