EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.16 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e793-il-1000000.txt Download as CSV file: xf-e793-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6845 0.09220 0.08979 -0.0576 1.0000 0.0141
-15.500 -0.7121 0.08350 0.08095 -0.0627 1.0000 0.0141
-15.250 -0.7354 0.07602 0.07334 -0.0671 1.0000 0.0141
-15.000 -0.7585 0.06905 0.06623 -0.0712 1.0000 0.0141
-14.750 -0.7752 0.06350 0.06057 -0.0742 1.0000 0.0140
-14.500 -0.7856 0.05916 0.05614 -0.0766 1.0000 0.0142
-14.250 -0.8003 0.05445 0.05133 -0.0789 1.0000 0.0141
-14.000 -0.8121 0.05031 0.04709 -0.0808 1.0000 0.0142
-13.750 -0.8239 0.04641 0.04309 -0.0823 1.0000 0.0143
-13.500 -0.8321 0.04310 0.03969 -0.0834 1.0000 0.0143
-13.250 -0.8423 0.03984 0.03634 -0.0841 1.0000 0.0144
-13.000 -0.8517 0.03700 0.03343 -0.0842 1.0000 0.0144
-12.750 -0.8630 0.03449 0.03083 -0.0837 1.0000 0.0145
-12.500 -0.8616 0.03177 0.02801 -0.0859 0.9987 0.0146
-12.250 -0.8388 0.02910 0.02519 -0.0920 0.9948 0.0147
-12.000 -0.8111 0.02699 0.02294 -0.0967 0.9915 0.0150
-11.750 -0.7826 0.02547 0.02131 -0.0997 0.9879 0.0152
-11.500 -0.7513 0.02425 0.01999 -0.1025 0.9855 0.0153
-11.250 -0.7181 0.02314 0.01878 -0.1054 0.9837 0.0155
-11.000 -0.6988 0.02095 0.01648 -0.1066 0.9784 0.0159
-10.750 -0.6704 0.01968 0.01517 -0.1083 0.9746 0.0162
-10.500 -0.6378 0.01864 0.01410 -0.1105 0.9722 0.0165
-10.250 -0.6128 0.01779 0.01321 -0.1109 0.9658 0.0167
-10.000 -0.5832 0.01695 0.01232 -0.1121 0.9609 0.0170
-9.750 -0.5547 0.01617 0.01149 -0.1129 0.9551 0.0173
-9.500 -0.5248 0.01543 0.01069 -0.1139 0.9474 0.0176
-9.250 -0.4868 0.01469 0.00990 -0.1165 0.9423 0.0180
-9.000 -0.4485 0.01402 0.00916 -0.1191 0.9339 0.0183
-8.750 -0.4085 0.01345 0.00851 -0.1220 0.9236 0.0187
-8.500 -0.3731 0.01285 0.00781 -0.1239 0.9079 0.0189
-8.250 -0.3454 0.01208 0.00691 -0.1245 0.8876 0.0196
-8.000 -0.3190 0.01168 0.00641 -0.1245 0.8683 0.0202
-7.750 -0.2933 0.01139 0.00601 -0.1241 0.8500 0.0208
-7.500 -0.2678 0.01112 0.00564 -0.1237 0.8323 0.0213
-7.250 -0.2423 0.01087 0.00528 -0.1233 0.8156 0.0218
-7.000 -0.2164 0.01065 0.00497 -0.1229 0.7997 0.0223
-6.750 -0.1908 0.01036 0.00458 -0.1225 0.7843 0.0231
-6.500 -0.1649 0.01008 0.00421 -0.1221 0.7691 0.0242
-6.250 -0.1385 0.00988 0.00395 -0.1218 0.7546 0.0254
-6.000 -0.1119 0.00972 0.00370 -0.1214 0.7404 0.0268
-5.750 -0.0855 0.00949 0.00342 -0.1211 0.7264 0.0303
-5.500 -0.0591 0.00919 0.00313 -0.1209 0.7126 0.0439
-5.250 -0.0328 0.00878 0.00284 -0.1208 0.6993 0.0758
-5.000 -0.0059 0.00849 0.00262 -0.1207 0.6866 0.1042
-4.750 0.0209 0.00826 0.00244 -0.1205 0.6742 0.1330
-4.500 0.0481 0.00805 0.00229 -0.1204 0.6615 0.1617
-4.250 0.0756 0.00787 0.00217 -0.1204 0.6492 0.1892
-4.000 0.1032 0.00774 0.00207 -0.1203 0.6379 0.2163
-3.500 0.1587 0.00757 0.00194 -0.1201 0.6146 0.2622
-3.250 0.1867 0.00755 0.00189 -0.1200 0.6037 0.2780
-2.750 0.2428 0.00751 0.00183 -0.1199 0.5824 0.3069
-2.500 0.2707 0.00751 0.00181 -0.1198 0.5721 0.3197
-2.250 0.2988 0.00751 0.00180 -0.1197 0.5617 0.3357
-2.000 0.3270 0.00752 0.00179 -0.1197 0.5525 0.3484
-1.500 0.3832 0.00756 0.00178 -0.1195 0.5334 0.3685
-1.000 0.4394 0.00762 0.00180 -0.1194 0.5160 0.3887
-0.750 0.4672 0.00767 0.00181 -0.1192 0.5073 0.3986
-0.500 0.4956 0.00769 0.00183 -0.1192 0.4993 0.4094
-0.250 0.5232 0.00775 0.00186 -0.1191 0.4912 0.4199
0.250 0.5793 0.00783 0.00193 -0.1190 0.4763 0.4429
0.500 0.6076 0.00786 0.00197 -0.1190 0.4695 0.4545
0.750 0.6354 0.00791 0.00202 -0.1189 0.4624 0.4669
1.000 0.6632 0.00797 0.00208 -0.1188 0.4558 0.4800
1.250 0.6913 0.00800 0.00213 -0.1187 0.4491 0.4936
1.500 0.7186 0.00809 0.00220 -0.1186 0.4420 0.5073
1.750 0.7468 0.00813 0.00227 -0.1185 0.4365 0.5218
2.000 0.7744 0.00819 0.00234 -0.1184 0.4302 0.5369
2.250 0.8017 0.00828 0.00243 -0.1183 0.4238 0.5527
2.500 0.8297 0.00832 0.00251 -0.1182 0.4180 0.5694
2.750 0.8569 0.00840 0.00261 -0.1180 0.4119 0.5865
3.000 0.8842 0.00848 0.00271 -0.1179 0.4064 0.6039
3.250 0.9118 0.00853 0.00281 -0.1178 0.4007 0.6228
3.500 0.9386 0.00863 0.00293 -0.1175 0.3945 0.6421
3.750 0.9658 0.00870 0.00304 -0.1174 0.3892 0.6626
4.000 0.9930 0.00876 0.00316 -0.1172 0.3839 0.6851
4.250 1.0193 0.00887 0.00330 -0.1169 0.3779 0.7087
4.500 1.0461 0.00894 0.00343 -0.1166 0.3727 0.7332
5.250 1.1230 0.00914 0.00388 -0.1152 0.3564 0.8349
5.500 1.1450 0.00914 0.00402 -0.1139 0.3509 0.8933
5.750 1.1679 0.00919 0.00414 -0.1128 0.3446 1.0000
6.000 1.1948 0.00932 0.00427 -0.1126 0.3396 1.0000
6.250 1.2209 0.00949 0.00442 -0.1123 0.3337 1.0000
6.500 1.2458 0.00972 0.00461 -0.1118 0.3274 1.0000
6.750 1.2722 0.00985 0.00476 -0.1116 0.3225 1.0000
7.000 1.2973 0.01005 0.00494 -0.1112 0.3165 1.0000
7.250 1.3219 0.01027 0.00514 -0.1106 0.3103 1.0000
7.500 1.3473 0.01044 0.00531 -0.1102 0.3047 1.0000
7.750 1.3710 0.01069 0.00553 -0.1095 0.2984 1.0000
8.000 1.3955 0.01089 0.00574 -0.1090 0.2933 1.0000
8.250 1.4196 0.01110 0.00595 -0.1084 0.2873 1.0000
8.500 1.4416 0.01140 0.00621 -0.1074 0.2807 1.0000
8.750 1.4658 0.01158 0.00642 -0.1068 0.2755 1.0000
9.000 1.4875 0.01185 0.00668 -0.1058 0.2691 1.0000
9.250 1.5082 0.01211 0.00694 -0.1046 0.2632 1.0000
9.500 1.5288 0.01237 0.00719 -0.1034 0.2567 1.0000
9.750 1.5468 0.01272 0.00752 -0.1018 0.2497 1.0000
10.000 1.5671 0.01298 0.00780 -0.1005 0.2433 1.0000
10.250 1.5838 0.01339 0.00818 -0.0987 0.2352 1.0000
10.500 1.6028 0.01371 0.00850 -0.0973 0.2278 1.0000
10.750 1.6184 0.01417 0.00893 -0.0954 0.2187 1.0000
11.000 1.6346 0.01461 0.00936 -0.0937 0.2098 1.0000
11.250 1.6498 0.01509 0.00983 -0.0918 0.2015 1.0000
11.500 1.6619 0.01572 0.01041 -0.0896 0.1910 1.0000
11.750 1.6728 0.01642 0.01106 -0.0872 0.1785 1.0000
12.000 1.6841 0.01710 0.01173 -0.0850 0.1683 1.0000
12.250 1.6931 0.01793 0.01252 -0.0825 0.1580 1.0000
12.500 1.6999 0.01889 0.01345 -0.0800 0.1478 1.0000
12.750 1.7052 0.01999 0.01450 -0.0774 0.1374 1.0000
13.000 1.7128 0.02100 0.01552 -0.0752 0.1297 1.0000
13.250 1.7158 0.02236 0.01685 -0.0728 0.1202 1.0000
13.500 1.7201 0.02371 0.01820 -0.0706 0.1133 1.0000
13.750 1.7241 0.02516 0.01966 -0.0687 0.1064 1.0000
14.000 1.7244 0.02697 0.02146 -0.0667 0.0990 1.0000
14.250 1.7282 0.02862 0.02313 -0.0651 0.0936 1.0000
14.500 1.7278 0.03070 0.02522 -0.0635 0.0881 1.0000
14.750 1.7303 0.03264 0.02720 -0.0623 0.0836 1.0000
15.000 1.7288 0.03504 0.02962 -0.0611 0.0786 1.0000
15.250 1.7275 0.03754 0.03216 -0.0602 0.0742 1.0000
15.500 1.7264 0.04014 0.03480 -0.0594 0.0703 1.0000
15.750 1.7206 0.04332 0.03801 -0.0588 0.0661 1.0000
16.000 1.7201 0.04608 0.04085 -0.0585 0.0633 1.0000
16.250 1.7160 0.04934 0.04416 -0.0583 0.0603 1.0000
16.500 1.7086 0.05309 0.04795 -0.0584 0.0570 1.0000
16.750 1.7052 0.05650 0.05143 -0.0586 0.0546 1.0000
17.000 1.6988 0.06039 0.05539 -0.0590 0.0521 1.0000
17.250 1.6889 0.06483 0.05988 -0.0597 0.0493 1.0000
17.500 1.6833 0.06884 0.06397 -0.0604 0.0474 1.0000
17.750 1.6766 0.07309 0.06830 -0.0613 0.0454 1.0000
18.000 1.6660 0.07798 0.07325 -0.0625 0.0431 1.0000
18.250 1.6561 0.08287 0.07821 -0.0638 0.0411 1.0000
18.500 1.6492 0.08743 0.08285 -0.0652 0.0393 1.0000
18.750 1.6404 0.09235 0.08784 -0.0667 0.0377 1.0000
19.000 1.6291 0.09772 0.09328 -0.0686 0.0359 1.0000
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Polar data table (+)
Polar graphs
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