EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 500,000 Max Cl/Cd: 100.76 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e793-il-500000-n5.txt Download as CSV file: xf-e793-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6373 0.10465 0.10149 -0.0515 1.0000 0.0132
-15.750 -0.6707 0.09444 0.09111 -0.0570 1.0000 0.0132
-15.500 -0.6878 0.08767 0.08423 -0.0607 1.0000 0.0133
-15.250 -0.7028 0.08155 0.07800 -0.0640 1.0000 0.0133
-15.000 -0.7182 0.07561 0.07195 -0.0671 1.0000 0.0133
-14.750 -0.7307 0.07041 0.06666 -0.0698 1.0000 0.0133
-14.500 -0.7391 0.06604 0.06223 -0.0721 1.0000 0.0135
-14.250 -0.7506 0.06155 0.05765 -0.0743 1.0000 0.0135
-14.000 -0.7613 0.05735 0.05335 -0.0761 1.0000 0.0136
-13.750 -0.7713 0.05341 0.04933 -0.0778 1.0000 0.0136
-13.500 -0.7791 0.04987 0.04571 -0.0791 1.0000 0.0137
-13.250 -0.7883 0.04639 0.04215 -0.0802 1.0000 0.0138
-13.000 -0.7962 0.04324 0.03893 -0.0809 1.0000 0.0139
-12.750 -0.8044 0.04030 0.03591 -0.0813 1.0000 0.0140
-12.500 -0.8152 0.03750 0.03303 -0.0810 1.0000 0.0140
-12.250 -0.8007 0.03442 0.02984 -0.0858 0.9972 0.0142
-12.000 -0.7811 0.03154 0.02682 -0.0911 0.9930 0.0144
-11.750 -0.7645 0.02895 0.02410 -0.0955 0.9864 0.0145
-11.500 -0.7380 0.02687 0.02187 -0.0999 0.9817 0.0148
-11.250 -0.7178 0.02532 0.02020 -0.1014 0.9742 0.0149
-11.000 -0.6950 0.02402 0.01880 -0.1027 0.9673 0.0151
-10.500 -0.6490 0.02190 0.01648 -0.1041 0.9500 0.0154
-10.250 -0.6215 0.02057 0.01509 -0.1058 0.9435 0.0157
-10.000 -0.5935 0.01947 0.01393 -0.1072 0.9345 0.0160
-9.750 -0.5557 0.01849 0.01288 -0.1103 0.9291 0.0163
-9.500 -0.5184 0.01764 0.01197 -0.1132 0.9198 0.0168
-9.250 -0.4781 0.01685 0.01110 -0.1165 0.9101 0.0173
-9.000 -0.4398 0.01615 0.01028 -0.1193 0.8966 0.0178
-8.750 -0.4071 0.01555 0.00956 -0.1208 0.8794 0.0183
-8.500 -0.3784 0.01505 0.00893 -0.1213 0.8607 0.0186
-8.250 -0.3523 0.01459 0.00834 -0.1214 0.8426 0.0189
-8.000 -0.3275 0.01408 0.00771 -0.1212 0.8252 0.0195
-7.750 -0.3025 0.01368 0.00722 -0.1209 0.8088 0.0200
-7.500 -0.2773 0.01335 0.00678 -0.1205 0.7932 0.0206
-7.250 -0.2520 0.01306 0.00637 -0.1201 0.7779 0.0213
-7.000 -0.2264 0.01279 0.00600 -0.1198 0.7630 0.0220
-6.750 -0.2006 0.01251 0.00563 -0.1194 0.7487 0.0229
-6.500 -0.1748 0.01223 0.00527 -0.1191 0.7347 0.0244
-6.250 -0.1487 0.01200 0.00496 -0.1188 0.7213 0.0261
-6.000 -0.1226 0.01176 0.00464 -0.1185 0.7082 0.0289
-5.750 -0.0963 0.01151 0.00435 -0.1183 0.6951 0.0345
-5.500 -0.0700 0.01122 0.00406 -0.1181 0.6822 0.0467
-5.250 -0.0435 0.01097 0.00381 -0.1179 0.6701 0.0618
-5.000 -0.0169 0.01073 0.00357 -0.1177 0.6581 0.0796
-4.750 0.0097 0.01047 0.00335 -0.1176 0.6457 0.1025
-4.500 0.0367 0.01023 0.00315 -0.1175 0.6343 0.1274
-4.250 0.0635 0.01000 0.00298 -0.1174 0.6231 0.1570
-4.000 0.0906 0.00981 0.00284 -0.1173 0.6117 0.1867
-3.750 0.1181 0.00968 0.00273 -0.1172 0.6013 0.2118
-3.500 0.1453 0.00958 0.00264 -0.1171 0.5908 0.2361
-3.250 0.1730 0.00950 0.00258 -0.1170 0.5802 0.2596
-3.000 0.2006 0.00945 0.00253 -0.1169 0.5705 0.2793
-2.750 0.2282 0.00942 0.00249 -0.1168 0.5608 0.2980
-2.500 0.2561 0.00940 0.00246 -0.1166 0.5514 0.3128
-2.000 0.3116 0.00941 0.00241 -0.1164 0.5333 0.3350
-1.750 0.3391 0.00945 0.00239 -0.1162 0.5247 0.3451
-1.500 0.3672 0.00945 0.00238 -0.1161 0.5161 0.3555
-1.250 0.3946 0.00950 0.00238 -0.1160 0.5078 0.3649
-1.000 0.4227 0.00952 0.00239 -0.1159 0.5002 0.3750
-0.750 0.4502 0.00956 0.00240 -0.1157 0.4923 0.3845
-0.500 0.4781 0.00960 0.00242 -0.1156 0.4848 0.3945
-0.250 0.5056 0.00964 0.00245 -0.1155 0.4773 0.4045
0.000 0.5334 0.00969 0.00248 -0.1154 0.4708 0.4146
0.250 0.5611 0.00973 0.00252 -0.1153 0.4635 0.4254
0.500 0.5883 0.00980 0.00257 -0.1151 0.4567 0.4358
0.750 0.6162 0.00985 0.00262 -0.1150 0.4503 0.4473
1.000 0.6434 0.00992 0.00269 -0.1148 0.4437 0.4586
1.250 0.6709 0.00998 0.00276 -0.1147 0.4377 0.4706
1.750 0.7252 0.01014 0.00293 -0.1143 0.4252 0.4966
2.000 0.7528 0.01020 0.00302 -0.1142 0.4196 0.5101
2.250 0.7799 0.01028 0.00311 -0.1140 0.4134 0.5238
2.500 0.8066 0.01039 0.00322 -0.1137 0.4076 0.5386
3.000 0.8608 0.01055 0.00345 -0.1133 0.3965 0.5690
3.250 0.8871 0.01066 0.00359 -0.1130 0.3910 0.5858
3.500 0.9141 0.01074 0.00371 -0.1128 0.3853 0.6026
3.750 0.9405 0.01085 0.00386 -0.1125 0.3797 0.6195
4.000 0.9665 0.01097 0.00402 -0.1121 0.3749 0.6383
4.250 0.9931 0.01106 0.00417 -0.1119 0.3696 0.6587
4.500 1.0188 0.01117 0.00434 -0.1114 0.3637 0.6796
4.750 1.0441 0.01131 0.00452 -0.1110 0.3587 0.7018
5.000 1.0701 0.01139 0.00469 -0.1106 0.3539 0.7276
5.250 1.0949 0.01151 0.00489 -0.1100 0.3485 0.7558
5.500 1.1185 0.01164 0.00509 -0.1091 0.3432 0.7885
5.750 1.1419 0.01169 0.00528 -0.1082 0.3385 0.8303
6.000 1.1597 0.01169 0.00545 -0.1060 0.3335 0.8996
6.500 1.2105 0.01202 0.00581 -0.1051 0.3225 1.0000
6.750 1.2347 0.01226 0.00603 -0.1045 0.3161 1.0000
7.000 1.2583 0.01252 0.00627 -0.1039 0.3106 1.0000
7.250 1.2827 0.01273 0.00650 -0.1033 0.3048 1.0000
7.500 1.3053 0.01301 0.00676 -0.1025 0.2986 1.0000
7.750 1.3284 0.01327 0.00702 -0.1017 0.2931 1.0000
8.000 1.3507 0.01353 0.00729 -0.1008 0.2865 1.0000
8.250 1.3704 0.01385 0.00759 -0.0995 0.2804 1.0000
8.500 1.3918 0.01410 0.00787 -0.0984 0.2741 1.0000
8.750 1.4107 0.01444 0.00820 -0.0970 0.2677 1.0000
9.000 1.4304 0.01476 0.00853 -0.0957 0.2620 1.0000
9.250 1.4495 0.01511 0.00889 -0.0943 0.2552 1.0000
9.500 1.4668 0.01552 0.00930 -0.0927 0.2489 1.0000
9.750 1.4854 0.01589 0.00969 -0.0913 0.2418 1.0000
10.000 1.5010 0.01638 0.01017 -0.0895 0.2350 1.0000
10.250 1.5187 0.01680 0.01061 -0.0880 0.2280 1.0000
10.500 1.5325 0.01738 0.01118 -0.0860 0.2204 1.0000
10.750 1.5483 0.01789 0.01171 -0.0844 0.2124 1.0000
11.000 1.5605 0.01858 0.01238 -0.0824 0.2040 1.0000
11.250 1.5729 0.01927 0.01309 -0.0805 0.1948 1.0000
11.500 1.5839 0.02007 0.01388 -0.0785 0.1862 1.0000
11.750 1.5920 0.02105 0.01484 -0.0762 0.1764 1.0000
12.000 1.5998 0.02209 0.01588 -0.0741 0.1657 1.0000
12.250 1.6062 0.02328 0.01705 -0.0720 0.1558 1.0000
12.500 1.6115 0.02459 0.01837 -0.0700 0.1477 1.0000
12.750 1.6162 0.02603 0.01981 -0.0681 0.1390 1.0000
13.000 1.6207 0.02756 0.02136 -0.0664 0.1322 1.0000
13.250 1.6233 0.02932 0.02313 -0.0648 0.1250 1.0000
13.500 1.6258 0.03117 0.02502 -0.0633 0.1182 1.0000
13.750 1.6247 0.03344 0.02729 -0.0620 0.1111 1.0000
14.000 1.6263 0.03557 0.02947 -0.0609 0.1051 1.0000
14.250 1.6233 0.03825 0.03217 -0.0599 0.0989 1.0000
14.500 1.6233 0.04076 0.03474 -0.0592 0.0937 1.0000
14.750 1.6206 0.04363 0.03766 -0.0587 0.0891 1.0000
15.000 1.6171 0.04673 0.04080 -0.0583 0.0843 1.0000
15.250 1.6125 0.05007 0.04419 -0.0582 0.0793 1.0000
15.500 1.6063 0.05371 0.04788 -0.0582 0.0756 1.0000
15.750 1.6035 0.05706 0.05131 -0.0584 0.0720 1.0000
16.000 1.5969 0.06101 0.05532 -0.0588 0.0683 1.0000
16.250 1.5894 0.06517 0.05955 -0.0595 0.0654 1.0000
16.500 1.5849 0.06906 0.06352 -0.0601 0.0623 1.0000
16.750 1.5772 0.07347 0.06800 -0.0611 0.0590 1.0000
17.000 1.5681 0.07818 0.07277 -0.0622 0.0563 1.0000
17.250 1.5625 0.08247 0.07715 -0.0633 0.0537 1.0000
17.500 1.5539 0.08731 0.08205 -0.0647 0.0506 1.0000
17.750 1.5444 0.09237 0.08718 -0.0663 0.0481 1.0000
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Polar data table (+)
Polar graphs
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