EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 100,000 Max Cl/Cd: 43.26 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e793-il-100000.txt Download as CSV file: xf-e793-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2978 0.11262 0.10780 -0.0409 1.0000 0.1476
-9.750 -0.3208 0.10943 0.10475 -0.0426 1.0000 0.1492
-9.500 -0.4196 0.07903 0.07443 -0.0582 1.0000 0.0797
-9.250 -0.4213 0.07690 0.07238 -0.0559 1.0000 0.0788
-9.000 -0.4424 0.07325 0.06884 -0.0547 1.0000 0.0774
-8.750 -0.4952 0.06847 0.06418 -0.0538 1.0000 0.0758
-8.500 -0.5570 0.06351 0.05924 -0.0548 1.0000 0.0742
-8.250 -0.6384 0.05276 0.04738 -0.0603 1.0000 0.0690
-8.000 -0.6131 0.04725 0.04149 -0.0656 0.9939 0.0684
-7.750 -0.5808 0.04236 0.03603 -0.0711 0.9855 0.0681
-7.500 -0.5451 0.03872 0.03170 -0.0758 0.9770 0.0689
-7.250 -0.5054 0.03559 0.02837 -0.0801 0.9706 0.0714
-7.000 -0.4690 0.03355 0.02615 -0.0828 0.9612 0.0738
-6.750 -0.4305 0.03154 0.02386 -0.0855 0.9528 0.0761
-6.250 -0.3525 0.02810 0.02015 -0.0904 0.9358 0.0846
-6.000 -0.3062 0.02655 0.01855 -0.0939 0.9299 0.0944
-5.750 -0.2734 0.02523 0.01730 -0.0951 0.9188 0.1070
-5.500 -0.2258 0.02337 0.01572 -0.0993 0.9136 0.1493
-5.250 -0.1935 0.02227 0.01496 -0.1009 0.9019 0.2124
-5.000 -0.1501 0.02200 0.01483 -0.1039 0.8938 0.2701
-4.750 -0.1088 0.02215 0.01501 -0.1061 0.8847 0.3145
-4.500 -0.0650 0.02209 0.01493 -0.1084 0.8771 0.3476
-4.250 -0.0249 0.02192 0.01474 -0.1101 0.8679 0.3738
-4.000 0.0133 0.02172 0.01447 -0.1114 0.8586 0.3972
-3.750 0.0541 0.02145 0.01421 -0.1129 0.8500 0.4184
-3.500 0.0869 0.02127 0.01400 -0.1132 0.8385 0.4370
-3.250 0.1297 0.02087 0.01353 -0.1151 0.8309 0.4566
-3.000 0.1581 0.02072 0.01332 -0.1147 0.8176 0.4723
-2.750 0.1892 0.02052 0.01304 -0.1148 0.8058 0.4882
-2.500 0.2264 0.02018 0.01259 -0.1159 0.7965 0.5047
-2.250 0.2529 0.02009 0.01242 -0.1153 0.7828 0.5197
-2.000 0.2808 0.02000 0.01226 -0.1149 0.7704 0.5344
-1.750 0.3122 0.01982 0.01202 -0.1149 0.7601 0.5485
-1.500 0.3391 0.01973 0.01189 -0.1143 0.7478 0.5624
-1.250 0.3651 0.01970 0.01182 -0.1137 0.7356 0.5768
-1.000 0.3948 0.01961 0.01163 -0.1136 0.7254 0.5924
-0.750 0.4215 0.01957 0.01154 -0.1131 0.7139 0.6080
-0.500 0.4469 0.01962 0.01155 -0.1124 0.7025 0.6240
-0.250 0.4774 0.01953 0.01136 -0.1124 0.6937 0.6411
0.000 0.5001 0.01962 0.01149 -0.1112 0.6818 0.6580
0.250 0.5256 0.01967 0.01153 -0.1105 0.6719 0.6758
0.500 0.5517 0.01967 0.01151 -0.1097 0.6625 0.6944
0.750 0.5741 0.01978 0.01168 -0.1084 0.6522 0.7138
1.000 0.6012 0.01976 0.01160 -0.1077 0.6441 0.7354
1.250 0.6217 0.01993 0.01184 -0.1062 0.6337 0.7590
1.500 0.6475 0.01988 0.01174 -0.1051 0.6265 0.7837
1.750 0.6652 0.02005 0.01203 -0.1030 0.6163 0.8119
2.000 0.6886 0.01997 0.01190 -0.1014 0.6095 0.8442
2.250 0.7007 0.02006 0.01216 -0.0980 0.6001 0.8826
2.500 0.7327 0.01985 0.01192 -0.0981 0.5930 0.9412
2.750 0.7748 0.02017 0.01223 -0.1021 0.5823 1.0000
3.000 0.8127 0.02040 0.01222 -0.1045 0.5755 1.0000
3.250 0.8367 0.02095 0.01278 -0.1046 0.5657 1.0000
3.500 0.8705 0.02119 0.01282 -0.1058 0.5591 1.0000
3.750 0.8924 0.02180 0.01347 -0.1053 0.5500 1.0000
4.000 0.9236 0.02208 0.01362 -0.1059 0.5433 1.0000
4.250 0.9460 0.02269 0.01425 -0.1053 0.5351 1.0000
4.500 0.9745 0.02304 0.01452 -0.1054 0.5280 1.0000
4.750 0.9997 0.02359 0.01507 -0.1052 0.5210 1.0000
5.000 1.0237 0.02411 0.01560 -0.1047 0.5133 1.0000
5.250 1.0560 0.02441 0.01576 -0.1054 0.5076 1.0000
5.500 1.0724 0.02523 0.01675 -0.1039 0.4992 1.0000
5.750 1.1025 0.02555 0.01698 -0.1042 0.4932 1.0000
6.000 1.1222 0.02634 0.01786 -0.1032 0.4860 1.0000
6.250 1.1470 0.02684 0.01838 -0.1028 0.4790 1.0000
6.500 1.1772 0.02726 0.01872 -0.1032 0.4736 1.0000
6.750 1.1911 0.02822 0.01987 -0.1014 0.4656 1.0000
7.000 1.2218 0.02850 0.02009 -0.1017 0.4599 1.0000
7.250 1.2383 0.02946 0.02118 -0.1003 0.4529 1.0000
7.500 1.2610 0.03004 0.02181 -0.0997 0.4461 1.0000
7.750 1.2933 0.03032 0.02201 -0.1002 0.4406 1.0000
8.000 1.3014 0.03153 0.02345 -0.0977 0.4326 1.0000
8.250 1.3338 0.03165 0.02350 -0.0982 0.4267 1.0000
8.500 1.3456 0.03277 0.02479 -0.0962 0.4195 1.0000
8.750 1.3684 0.03324 0.02532 -0.0955 0.4126 1.0000
9.000 1.3963 0.03362 0.02568 -0.0955 0.4065 1.0000
9.250 1.4036 0.03477 0.02704 -0.0929 0.3988 1.0000
9.500 1.4436 0.03448 0.02661 -0.0942 0.3927 1.0000
9.750 1.4414 0.03606 0.02848 -0.0905 0.3850 1.0000
10.000 1.4739 0.03593 0.02830 -0.0909 0.3780 1.0000
10.250 1.4817 0.03705 0.02958 -0.0884 0.3708 1.0000
10.500 1.5034 0.03732 0.02990 -0.0874 0.3633 1.0000
10.750 1.5217 0.03789 0.03053 -0.0862 0.3562 1.0000
11.000 1.5315 0.03862 0.03139 -0.0838 0.3485 1.0000
11.250 1.5582 0.03873 0.03148 -0.0835 0.3411 1.0000
11.500 1.5563 0.03989 0.03283 -0.0798 0.3335 1.0000
11.750 1.5877 0.03970 0.03258 -0.0799 0.3256 1.0000
12.000 1.5730 0.04121 0.03431 -0.0747 0.3186 1.0000
12.250 1.6075 0.04079 0.03379 -0.0752 0.3101 1.0000
12.500 1.5853 0.04272 0.03596 -0.0695 0.3035 1.0000
12.750 1.6185 0.04222 0.03536 -0.0697 0.2945 1.0000
13.000 1.5923 0.04460 0.03799 -0.0645 0.2881 1.0000
13.250 1.2067 0.09140 0.08537 -0.0654 0.2784 1.0000
13.500 1.2719 0.08356 0.07765 -0.0616 0.2760 1.0000
13.750 1.6159 0.04701 0.04046 -0.0590 0.2632 1.0000
14.000 1.5896 0.05034 0.04401 -0.0558 0.2566 1.0000
14.250 1.6056 0.05076 0.04436 -0.0548 0.2475 1.0000
14.500 1.5838 0.05424 0.04803 -0.0528 0.2406 1.0000
14.750 1.5905 0.05557 0.04936 -0.0517 0.2320 1.0000
15.000 1.5770 0.05881 0.05271 -0.0507 0.2245 1.0000
15.250 1.5730 0.06141 0.05535 -0.0499 0.2168 1.0000
15.500 1.5690 0.06402 0.05800 -0.0494 0.2087 1.0000
15.750 1.5544 0.06811 0.06221 -0.0493 0.2020 1.0000
16.000 1.5558 0.07037 0.06447 -0.0491 0.1938 1.0000
16.250 1.5365 0.07548 0.06972 -0.0497 0.1877 1.0000
16.500 1.5264 0.07954 0.07386 -0.0503 0.1808 1.0000
16.750 1.5212 0.08318 0.07754 -0.0508 0.1741 1.0000
17.000 1.4832 0.09180 0.08640 -0.0536 0.1696 1.0000
17.250 1.5105 0.09074 0.08518 -0.0523 0.1610 1.0000
17.500 1.4554 0.10266 0.09744 -0.0572 0.1583 1.0000
17.750 1.5074 0.09751 0.09202 -0.0538 0.1484 1.0000
18.000 1.4490 0.11041 0.10528 -0.0597 0.1465 1.0000
18.250 1.0583 0.20708 0.20187 -0.1161 0.1451 1.0000
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