EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 200,000 Max Cl/Cd: 72.6 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e793-il-200000-n5.txt Download as CSV file: xf-e793-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 793 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5221 0.08687 0.08265 -0.0601 1.0000 0.0215
-13.000 -0.5766 0.07364 0.06918 -0.0685 1.0000 0.0211
-12.750 -0.6073 0.06581 0.06117 -0.0734 1.0000 0.0210
-12.500 -0.6299 0.05986 0.05507 -0.0768 1.0000 0.0210
-12.250 -0.6496 0.05479 0.04985 -0.0793 1.0000 0.0209
-12.000 -0.6665 0.05059 0.04552 -0.0810 1.0000 0.0210
-11.750 -0.6824 0.04703 0.04185 -0.0818 1.0000 0.0210
-11.500 -0.6991 0.04407 0.03878 -0.0816 1.0000 0.0211
-11.250 -0.7200 0.04173 0.03637 -0.0798 1.0000 0.0211
-11.000 -0.7247 0.03906 0.03353 -0.0814 0.9966 0.0212
-10.750 -0.7020 0.03611 0.03030 -0.0862 0.9897 0.0216
-10.500 -0.6762 0.03365 0.02755 -0.0901 0.9835 0.0222
-10.250 -0.6533 0.03169 0.02536 -0.0922 0.9755 0.0227
-10.000 -0.6258 0.03002 0.02366 -0.0944 0.9697 0.0232
-9.750 -0.6013 0.02862 0.02218 -0.0956 0.9612 0.0236
-9.500 -0.5755 0.02725 0.02074 -0.0968 0.9531 0.0241
-9.250 -0.5470 0.02593 0.01931 -0.0983 0.9460 0.0246
-9.000 -0.5212 0.02473 0.01802 -0.0990 0.9370 0.0251
-8.750 -0.4900 0.02353 0.01670 -0.1007 0.9307 0.0258
-8.500 -0.4615 0.02249 0.01555 -0.1017 0.9214 0.0264
-8.250 -0.4269 0.02133 0.01432 -0.1041 0.9150 0.0272
-8.000 -0.3955 0.02038 0.01332 -0.1057 0.9055 0.0283
-7.750 -0.3585 0.01949 0.01235 -0.1082 0.8980 0.0298
-7.500 -0.3260 0.01872 0.01146 -0.1096 0.8869 0.0313
-7.250 -0.2913 0.01786 0.01053 -0.1116 0.8763 0.0328
-7.000 -0.2560 0.01714 0.00971 -0.1135 0.8649 0.0349
-6.750 -0.2241 0.01651 0.00898 -0.1147 0.8512 0.0376
-6.500 -0.1931 0.01592 0.00830 -0.1156 0.8377 0.0420
-6.250 -0.1630 0.01537 0.00769 -0.1163 0.8238 0.0501
-6.000 -0.1342 0.01479 0.00711 -0.1168 0.8099 0.0654
-5.750 -0.1059 0.01429 0.00661 -0.1171 0.7960 0.0866
-5.500 -0.0788 0.01387 0.00620 -0.1172 0.7816 0.1103
-5.250 -0.0518 0.01350 0.00586 -0.1172 0.7677 0.1373
-5.000 -0.0247 0.01316 0.00556 -0.1172 0.7542 0.1693
-4.750 0.0023 0.01288 0.00533 -0.1172 0.7410 0.2064
-4.250 0.0566 0.01257 0.00505 -0.1169 0.7148 0.2674
-4.000 0.0839 0.01250 0.00492 -0.1167 0.7020 0.2876
-3.750 0.1113 0.01246 0.00480 -0.1165 0.6898 0.3040
-3.500 0.1386 0.01244 0.00469 -0.1163 0.6777 0.3197
-3.250 0.1658 0.01241 0.00461 -0.1160 0.6655 0.3343
-3.000 0.1931 0.01240 0.00452 -0.1157 0.6540 0.3474
-2.750 0.2204 0.01241 0.00442 -0.1155 0.6428 0.3602
-2.500 0.2475 0.01239 0.00437 -0.1152 0.6313 0.3716
-2.250 0.2747 0.01239 0.00430 -0.1149 0.6208 0.3828
-2.000 0.3019 0.01242 0.00424 -0.1147 0.6103 0.3942
-1.750 0.3291 0.01242 0.00422 -0.1144 0.5998 0.4048
-1.500 0.3562 0.01246 0.00417 -0.1142 0.5902 0.4158
-1.250 0.3834 0.01248 0.00416 -0.1139 0.5802 0.4269
-1.000 0.4105 0.01251 0.00415 -0.1136 0.5709 0.4378
-0.750 0.4376 0.01256 0.00415 -0.1134 0.5615 0.4493
-0.500 0.4647 0.01260 0.00417 -0.1131 0.5528 0.4610
-0.250 0.4916 0.01265 0.00419 -0.1128 0.5440 0.4727
0.000 0.5187 0.01271 0.00423 -0.1126 0.5355 0.4851
0.250 0.5455 0.01278 0.00428 -0.1123 0.5272 0.4981
0.500 0.5724 0.01284 0.00434 -0.1120 0.5194 0.5112
0.750 0.5991 0.01292 0.00441 -0.1117 0.5114 0.5251
1.000 0.6259 0.01300 0.00449 -0.1114 0.5039 0.5395
1.250 0.6526 0.01309 0.00458 -0.1111 0.4963 0.5548
1.750 0.7056 0.01327 0.00480 -0.1104 0.4819 0.5868
2.000 0.7317 0.01339 0.00491 -0.1100 0.4753 0.6039
2.250 0.7581 0.01348 0.00506 -0.1097 0.4686 0.6220
2.500 0.7840 0.01359 0.00520 -0.1092 0.4618 0.6407
2.750 0.8096 0.01371 0.00535 -0.1087 0.4556 0.6603
3.000 0.8351 0.01380 0.00552 -0.1082 0.4488 0.6817
3.250 0.8601 0.01393 0.00568 -0.1076 0.4430 0.7048
3.500 0.8850 0.01404 0.00587 -0.1069 0.4369 0.7295
3.750 0.9090 0.01414 0.00605 -0.1060 0.4305 0.7573
4.000 0.9319 0.01427 0.00622 -0.1049 0.4251 0.7890
4.500 0.9741 0.01435 0.00654 -0.1018 0.4136 0.8873
4.750 1.0020 0.01447 0.00666 -0.1018 0.4081 1.0000
5.000 1.0283 0.01468 0.00689 -0.1016 0.4020 1.0000
5.250 1.0539 0.01493 0.00711 -0.1013 0.3964 1.0000
5.500 1.0791 0.01522 0.00735 -0.1009 0.3912 1.0000
5.750 1.1045 0.01545 0.00762 -0.1006 0.3851 1.0000
6.000 1.1292 0.01572 0.00788 -0.1001 0.3796 1.0000
6.250 1.1537 0.01603 0.00815 -0.0996 0.3747 1.0000
6.500 1.1782 0.01629 0.00846 -0.0992 0.3689 1.0000
6.750 1.2019 0.01658 0.00875 -0.0985 0.3632 1.0000
7.000 1.2253 0.01691 0.00907 -0.0979 0.3583 1.0000
7.250 1.2487 0.01720 0.00942 -0.0972 0.3523 1.0000
7.500 1.2709 0.01753 0.00974 -0.0964 0.3465 1.0000
7.750 1.2930 0.01787 0.01011 -0.0955 0.3410 1.0000
8.000 1.3146 0.01819 0.01048 -0.0946 0.3347 1.0000
8.250 1.3348 0.01857 0.01084 -0.0934 0.3290 1.0000
8.500 1.3555 0.01892 0.01127 -0.0924 0.3231 1.0000
8.750 1.3741 0.01929 0.01167 -0.0909 0.3169 1.0000
9.000 1.3911 0.01971 0.01208 -0.0893 0.3114 1.0000
9.250 1.4090 0.02010 0.01256 -0.0878 0.3048 1.0000
9.500 1.4247 0.02056 0.01304 -0.0860 0.2987 1.0000
9.750 1.4408 0.02103 0.01357 -0.0843 0.2926 1.0000
10.000 1.4561 0.02153 0.01413 -0.0826 0.2860 1.0000
10.250 1.4696 0.02212 0.01472 -0.0806 0.2803 1.0000
10.500 1.4845 0.02267 0.01538 -0.0790 0.2735 1.0000
10.750 1.4964 0.02335 0.01607 -0.0770 0.2672 1.0000
11.000 1.5092 0.02403 0.01684 -0.0752 0.2605 1.0000
11.250 1.5197 0.02482 0.01768 -0.0732 0.2536 1.0000
11.500 1.5299 0.02568 0.01860 -0.0714 0.2469 1.0000
11.750 1.5391 0.02664 0.01962 -0.0695 0.2395 1.0000
12.000 1.5467 0.02773 0.02075 -0.0676 0.2327 1.0000
12.250 1.5539 0.02890 0.02200 -0.0659 0.2248 1.0000
12.500 1.5592 0.03026 0.02340 -0.0642 0.2174 1.0000
12.750 1.5638 0.03176 0.02496 -0.0626 0.2093 1.0000
13.000 1.5672 0.03342 0.02668 -0.0611 0.2015 1.0000
13.250 1.5683 0.03536 0.02866 -0.0597 0.1933 1.0000
13.500 1.5700 0.03737 0.03073 -0.0585 0.1851 1.0000
13.750 1.5671 0.03987 0.03326 -0.0574 0.1774 1.0000
14.000 1.5672 0.04224 0.03570 -0.0566 0.1690 1.0000
14.250 1.5625 0.04517 0.03867 -0.0559 0.1618 1.0000
14.500 1.5595 0.04809 0.04167 -0.0555 0.1540 1.0000
14.750 1.5535 0.05145 0.04507 -0.0553 0.1476 1.0000
15.000 1.5484 0.05485 0.04855 -0.0553 0.1406 1.0000
15.250 1.5406 0.05872 0.05246 -0.0555 0.1348 1.0000
15.500 1.5355 0.06238 0.05621 -0.0559 0.1287 1.0000
15.750 1.5259 0.06673 0.06061 -0.0565 0.1237 1.0000
16.000 1.5212 0.07059 0.06456 -0.0572 0.1185 1.0000
16.250 1.5129 0.07502 0.06906 -0.0582 0.1134 1.0000
16.500 1.5045 0.07957 0.07367 -0.0593 0.1092 1.0000
16.750 1.4991 0.08380 0.07801 -0.0604 0.1044 1.0000
17.000 1.4903 0.08863 0.08289 -0.0618 0.1003 1.0000
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Polar data table (+)
Polar graphs
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