EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 200,000 Max Cl/Cd: 69.69 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e793-il-200000.txt Download as CSV file: xf-e793-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2551 0.11141 0.10817 -0.0459 1.0000 0.0799
-11.000 -0.5014 0.06877 0.06500 -0.0708 1.0000 0.0431
-10.750 -0.5244 0.06354 0.05976 -0.0726 1.0000 0.0426
-10.500 -0.5564 0.05870 0.05489 -0.0741 1.0000 0.0421
-10.250 -0.5920 0.05559 0.05177 -0.0729 1.0000 0.0419
-10.000 -0.6294 0.05405 0.05025 -0.0694 1.0000 0.0417
-9.750 -0.6550 0.05104 0.04710 -0.0688 0.9990 0.0414
-9.500 -0.6424 0.04321 0.03865 -0.0786 0.9891 0.0402
-9.250 -0.6185 0.03772 0.03254 -0.0848 0.9823 0.0397
-9.000 -0.5912 0.03438 0.02879 -0.0881 0.9744 0.0399
-8.750 -0.5574 0.03193 0.02600 -0.0914 0.9689 0.0410
-8.500 -0.5249 0.02977 0.02351 -0.0938 0.9616 0.0418
-8.250 -0.4856 0.02765 0.02108 -0.0970 0.9580 0.0425
-8.000 -0.4555 0.02608 0.01927 -0.0981 0.9490 0.0431
-7.750 -0.4164 0.02414 0.01722 -0.1007 0.9453 0.0442
-7.500 -0.3853 0.02279 0.01591 -0.1017 0.9370 0.0455
-7.250 -0.3459 0.02160 0.01470 -0.1042 0.9323 0.0476
-7.000 -0.3022 0.02053 0.01350 -0.1074 0.9294 0.0505
-6.750 -0.2727 0.01924 0.01228 -0.1081 0.9197 0.0532
-6.500 -0.2301 0.01814 0.01116 -0.1112 0.9154 0.0576
-6.250 -0.1967 0.01703 0.01007 -0.1126 0.9061 0.0635
-6.000 -0.1568 0.01575 0.00885 -0.1154 0.8993 0.0823
-5.750 -0.1248 0.01438 0.00782 -0.1170 0.8881 0.1417
-5.500 -0.0862 0.01365 0.00723 -0.1193 0.8793 0.1969
-5.250 -0.0537 0.01329 0.00692 -0.1202 0.8666 0.2334
-5.000 -0.0222 0.01310 0.00671 -0.1208 0.8530 0.2641
-4.750 0.0094 0.01304 0.00656 -0.1212 0.8395 0.2932
-4.500 0.0400 0.01301 0.00650 -0.1215 0.8262 0.3179
-4.250 0.0704 0.01302 0.00639 -0.1217 0.8129 0.3385
-4.000 0.0979 0.01301 0.00631 -0.1214 0.7982 0.3552
-3.750 0.1252 0.01299 0.00622 -0.1210 0.7838 0.3701
-3.500 0.1528 0.01298 0.00613 -0.1207 0.7699 0.3849
-3.250 0.1807 0.01298 0.00603 -0.1204 0.7567 0.3993
-3.000 0.2090 0.01300 0.00590 -0.1202 0.7441 0.4134
-2.750 0.2356 0.01298 0.00585 -0.1197 0.7305 0.4256
-2.500 0.2624 0.01296 0.00579 -0.1192 0.7174 0.4376
-2.250 0.2899 0.01296 0.00569 -0.1190 0.7052 0.4503
-1.750 0.3441 0.01297 0.00559 -0.1182 0.6811 0.4743
-1.500 0.3712 0.01298 0.00554 -0.1179 0.6695 0.4867
-1.250 0.3992 0.01304 0.00548 -0.1177 0.6591 0.5001
-1.000 0.4254 0.01303 0.00549 -0.1172 0.6473 0.5121
-0.750 0.4524 0.01306 0.00549 -0.1169 0.6369 0.5250
-0.500 0.4800 0.01312 0.00547 -0.1166 0.6271 0.5390
-0.250 0.5066 0.01316 0.00550 -0.1163 0.6162 0.5537
0.000 0.5339 0.01323 0.00553 -0.1160 0.6072 0.5683
0.250 0.5602 0.01326 0.00559 -0.1155 0.5972 0.5834
0.500 0.5872 0.01334 0.00565 -0.1152 0.5883 0.5995
0.750 0.6137 0.01339 0.00572 -0.1148 0.5790 0.6166
1.000 0.6403 0.01348 0.00582 -0.1144 0.5705 0.6347
1.250 0.6668 0.01355 0.00590 -0.1140 0.5619 0.6540
1.500 0.6932 0.01366 0.00602 -0.1136 0.5537 0.6748
1.750 0.7188 0.01372 0.00613 -0.1130 0.5454 0.6953
2.000 0.7446 0.01382 0.00627 -0.1124 0.5380 0.7178
2.250 0.7697 0.01390 0.00640 -0.1117 0.5299 0.7434
2.500 0.7945 0.01400 0.00654 -0.1108 0.5230 0.7693
2.750 0.8171 0.01404 0.00670 -0.1096 0.5151 0.7993
3.000 0.8397 0.01412 0.00679 -0.1082 0.5089 0.8347
3.250 0.8577 0.01411 0.00693 -0.1058 0.5017 0.8819
3.500 0.8881 0.01404 0.00690 -0.1060 0.4944 1.0000
3.750 0.9179 0.01433 0.00710 -0.1067 0.4875 1.0000
4.000 0.9459 0.01456 0.00729 -0.1070 0.4803 1.0000
4.250 0.9753 0.01488 0.00746 -0.1074 0.4743 1.0000
4.500 1.0007 0.01510 0.00774 -0.1071 0.4668 1.0000
4.750 1.0283 0.01536 0.00792 -0.1071 0.4606 1.0000
5.000 1.0551 0.01568 0.00822 -0.1071 0.4544 1.0000
5.250 1.0809 0.01594 0.00849 -0.1068 0.4476 1.0000
5.500 1.1090 0.01627 0.00870 -0.1069 0.4419 1.0000
5.750 1.1332 0.01656 0.00907 -0.1063 0.4353 1.0000
6.000 1.1592 0.01684 0.00934 -0.1061 0.4292 1.0000
6.250 1.1863 0.01721 0.00964 -0.1061 0.4236 1.0000
6.500 1.2096 0.01749 0.01002 -0.1053 0.4170 1.0000
6.750 1.2357 0.01780 0.01029 -0.1051 0.4112 1.0000
7.000 1.2605 0.01817 0.01068 -0.1047 0.4053 1.0000
7.250 1.2837 0.01847 0.01103 -0.1040 0.3987 1.0000
7.500 1.3102 0.01880 0.01130 -0.1038 0.3931 1.0000
7.750 1.3317 0.01915 0.01176 -0.1028 0.3866 1.0000
8.000 1.3550 0.01945 0.01207 -0.1021 0.3803 1.0000
8.250 1.3803 0.01985 0.01243 -0.1018 0.3746 1.0000
8.500 1.3997 0.02017 0.01289 -0.1005 0.3678 1.0000
8.750 1.4232 0.02049 0.01317 -0.0999 0.3618 1.0000
9.000 1.4436 0.02090 0.01366 -0.0988 0.3554 1.0000
9.250 1.4634 0.02122 0.01404 -0.0975 0.3487 1.0000
9.500 1.4869 0.02163 0.01440 -0.0969 0.3428 1.0000
9.750 1.5020 0.02200 0.01493 -0.0949 0.3359 1.0000
10.000 1.5224 0.02237 0.01528 -0.0939 0.3297 1.0000
10.250 1.5385 0.02284 0.01585 -0.0921 0.3232 1.0000
10.500 1.5534 0.02322 0.01630 -0.0902 0.3164 1.0000
10.750 1.5703 0.02369 0.01676 -0.0886 0.3101 1.0000
11.250 1.5938 0.02463 0.01779 -0.0838 0.2969 1.0000
11.500 1.5988 0.02524 0.01857 -0.0805 0.2901 1.0000
11.750 1.6082 0.02582 0.01918 -0.0780 0.2833 1.0000
12.000 1.6150 0.02658 0.02002 -0.0753 0.2762 1.0000
12.250 1.6206 0.02736 0.02087 -0.0727 0.2690 1.0000
12.500 1.6262 0.02829 0.02187 -0.0702 0.2617 1.0000
12.750 1.6292 0.02934 0.02300 -0.0677 0.2540 1.0000
13.000 1.6326 0.03055 0.02427 -0.0654 0.2465 1.0000
13.250 1.6336 0.03194 0.02572 -0.0632 0.2384 1.0000
13.500 1.6342 0.03353 0.02739 -0.0612 0.2304 1.0000
13.750 1.6335 0.03529 0.02917 -0.0594 0.2223 1.0000
14.000 1.6316 0.03734 0.03133 -0.0578 0.2137 1.0000
14.250 1.6290 0.03954 0.03350 -0.0564 0.2059 1.0000
14.500 1.6249 0.04208 0.03620 -0.0553 0.1971 1.0000
14.750 1.6201 0.04480 0.03892 -0.0544 0.1894 1.0000
15.000 1.6141 0.04782 0.04202 -0.0538 0.1811 1.0000
15.250 1.6078 0.05102 0.04527 -0.0534 0.1735 1.0000
15.500 1.6004 0.05452 0.04880 -0.0532 0.1660 1.0000
15.750 1.5934 0.05812 0.05246 -0.0532 0.1588 1.0000
16.000 1.5853 0.06197 0.05633 -0.0535 0.1520 1.0000
16.250 1.5780 0.06590 0.06033 -0.0539 0.1454 1.0000
16.500 1.5699 0.07001 0.06448 -0.0546 0.1391 1.0000
16.750 1.5629 0.07409 0.06860 -0.0553 0.1332 1.0000
17.000 1.5553 0.07842 0.07302 -0.0563 0.1274 1.0000
17.250 1.5502 0.08232 0.07687 -0.0570 0.1220 1.0000
17.500 1.5423 0.08694 0.08165 -0.0584 0.1168 1.0000
17.750 1.5369 0.09103 0.08570 -0.0595 0.1118 1.0000
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