EPPLER 793 AIRFOIL (e793-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 793 AIRFOIL (e793-il) Reynolds number: 500,000 Max Cl/Cd: 102.55 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e793-il-500000.txt Download as CSV file: xf-e793-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5117 0.09570 0.09304 -0.0547 1.0000 0.0224
-13.500 -0.5681 0.08106 0.07825 -0.0633 1.0000 0.0218
-13.250 -0.6129 0.07024 0.06726 -0.0703 1.0000 0.0214
-13.000 -0.6453 0.06238 0.05925 -0.0754 1.0000 0.0212
-12.750 -0.6736 0.05582 0.05252 -0.0794 1.0000 0.0211
-12.500 -0.7008 0.05006 0.04660 -0.0825 1.0000 0.0209
-12.250 -0.7197 0.04603 0.04245 -0.0839 1.0000 0.0209
-12.000 -0.7425 0.04240 0.03868 -0.0842 1.0000 0.0208
-11.750 -0.7659 0.04004 0.03625 -0.0824 1.0000 0.0208
-11.500 -0.7864 0.03755 0.03362 -0.0819 0.9984 0.0208
-11.250 -0.7610 0.03398 0.02976 -0.0882 0.9938 0.0210
-11.000 -0.7349 0.03157 0.02711 -0.0919 0.9887 0.0214
-10.750 -0.7052 0.02943 0.02473 -0.0954 0.9849 0.0218
-10.500 -0.6742 0.02759 0.02267 -0.0985 0.9817 0.0221
-10.250 -0.6466 0.02611 0.02100 -0.1001 0.9758 0.0224
-10.000 -0.6133 0.02461 0.01933 -0.1027 0.9726 0.0226
-9.750 -0.5865 0.02261 0.01725 -0.1039 0.9677 0.0229
-9.500 -0.5574 0.02116 0.01577 -0.1052 0.9622 0.0233
-9.250 -0.5229 0.01999 0.01458 -0.1074 0.9591 0.0238
-9.000 -0.4956 0.01904 0.01358 -0.1079 0.9515 0.0242
-8.750 -0.4625 0.01807 0.01256 -0.1096 0.9468 0.0249
-8.500 -0.4297 0.01721 0.01163 -0.1110 0.9411 0.0255
-8.250 -0.3959 0.01643 0.01079 -0.1126 0.9339 0.0262
-8.000 -0.3552 0.01563 0.00990 -0.1156 0.9294 0.0269
-7.750 -0.3230 0.01454 0.00878 -0.1173 0.9185 0.0278
-7.500 -0.2864 0.01382 0.00801 -0.1194 0.9082 0.0288
-7.250 -0.2506 0.01323 0.00734 -0.1213 0.8957 0.0299
-7.000 -0.2186 0.01277 0.00677 -0.1223 0.8805 0.0311
-6.500 -0.1629 0.01187 0.00567 -0.1225 0.8477 0.0349
-6.250 -0.1360 0.01155 0.00526 -0.1223 0.8315 0.0379
-6.000 -0.1098 0.01116 0.00482 -0.1220 0.8158 0.0448
-5.750 -0.0846 0.01056 0.00431 -0.1218 0.8003 0.0737
-5.500 -0.0590 0.01008 0.00395 -0.1216 0.7853 0.1129
-5.250 -0.0328 0.00976 0.00370 -0.1214 0.7709 0.1465
-5.000 -0.0063 0.00952 0.00349 -0.1212 0.7567 0.1787
-4.750 0.0203 0.00933 0.00332 -0.1210 0.7428 0.2090
-4.500 0.0472 0.00919 0.00319 -0.1207 0.7290 0.2347
-4.250 0.0743 0.00910 0.00310 -0.1205 0.7154 0.2586
-4.000 0.1015 0.00904 0.00302 -0.1203 0.7023 0.2789
-3.750 0.1289 0.00902 0.00295 -0.1200 0.6897 0.2958
-3.250 0.1836 0.00900 0.00285 -0.1195 0.6644 0.3276
-3.000 0.2111 0.00901 0.00281 -0.1193 0.6526 0.3421
-2.750 0.2384 0.00902 0.00278 -0.1191 0.6411 0.3564
-2.500 0.2658 0.00902 0.00275 -0.1189 0.6292 0.3685
-2.250 0.2935 0.00905 0.00272 -0.1187 0.6180 0.3795
-2.000 0.3208 0.00908 0.00270 -0.1184 0.6075 0.3903
-1.750 0.3484 0.00909 0.00268 -0.1183 0.5965 0.4008
-1.500 0.3761 0.00913 0.00267 -0.1181 0.5862 0.4118
-1.250 0.4033 0.00916 0.00267 -0.1178 0.5762 0.4224
-1.000 0.4311 0.00918 0.00267 -0.1177 0.5665 0.4334
-0.750 0.4584 0.00924 0.00268 -0.1175 0.5572 0.4449
-0.500 0.4861 0.00926 0.00270 -0.1173 0.5476 0.4564
-0.250 0.5135 0.00932 0.00273 -0.1171 0.5391 0.4684
0.000 0.5411 0.00936 0.00276 -0.1170 0.5303 0.4813
0.250 0.5684 0.00942 0.00281 -0.1168 0.5222 0.4942
0.500 0.5959 0.00946 0.00286 -0.1166 0.5137 0.5076
0.750 0.6231 0.00954 0.00292 -0.1164 0.5063 0.5220
1.000 0.6507 0.00959 0.00299 -0.1163 0.4984 0.5370
1.250 0.6775 0.00970 0.00306 -0.1160 0.4911 0.5528
1.500 0.7052 0.00972 0.00315 -0.1159 0.4837 0.5693
1.750 0.7320 0.00981 0.00324 -0.1156 0.4768 0.5865
2.000 0.7593 0.00988 0.00334 -0.1154 0.4701 0.6046
2.250 0.7863 0.00995 0.00344 -0.1152 0.4631 0.6233
2.500 0.8128 0.01006 0.00356 -0.1148 0.4566 0.6431
2.750 0.8399 0.01010 0.00368 -0.1146 0.4502 0.6640
3.000 0.8661 0.01020 0.00381 -0.1142 0.4439 0.6862
3.250 0.8926 0.01028 0.00395 -0.1139 0.4377 0.7105
3.500 0.9187 0.01034 0.00409 -0.1135 0.4313 0.7364
3.750 0.9438 0.01048 0.00425 -0.1129 0.4254 0.7643
4.000 0.9692 0.01050 0.00440 -0.1123 0.4198 0.7973
4.250 0.9925 0.01054 0.00454 -0.1112 0.4138 0.8378
4.500 1.0105 0.01058 0.00468 -0.1090 0.4083 0.8993
4.750 1.0385 0.01055 0.00476 -0.1089 0.4027 1.0000
5.000 1.0651 0.01074 0.00490 -0.1087 0.3970 1.0000
5.250 1.0909 0.01098 0.00509 -0.1084 0.3913 1.0000
5.500 1.1176 0.01112 0.00525 -0.1082 0.3856 1.0000
5.750 1.1433 0.01132 0.00543 -0.1078 0.3800 1.0000
6.000 1.1684 0.01157 0.00564 -0.1074 0.3745 1.0000
6.250 1.1944 0.01172 0.00582 -0.1071 0.3686 1.0000
6.500 1.2190 0.01196 0.00602 -0.1066 0.3628 1.0000
6.750 1.2436 0.01219 0.00625 -0.1060 0.3570 1.0000
7.000 1.2685 0.01237 0.00646 -0.1056 0.3511 1.0000
7.250 1.2917 0.01266 0.00669 -0.1048 0.3453 1.0000
7.500 1.3160 0.01287 0.00694 -0.1042 0.3397 1.0000
7.750 1.3395 0.01309 0.00718 -0.1035 0.3337 1.0000
8.000 1.3609 0.01344 0.00747 -0.1025 0.3276 1.0000
8.250 1.3848 0.01361 0.00772 -0.1019 0.3219 1.0000
8.500 1.4060 0.01389 0.00799 -0.1008 0.3158 1.0000
8.750 1.4259 0.01421 0.00830 -0.0995 0.3103 1.0000
9.000 1.4470 0.01444 0.00859 -0.0983 0.3045 1.0000
9.250 1.4650 0.01479 0.00892 -0.0967 0.2985 1.0000
9.500 1.4845 0.01509 0.00926 -0.0954 0.2929 1.0000
9.750 1.5033 0.01541 0.00961 -0.0940 0.2865 1.0000
10.000 1.5192 0.01586 0.01004 -0.0921 0.2805 1.0000
10.250 1.5390 0.01615 0.01040 -0.0909 0.2743 1.0000
10.500 1.5543 0.01661 0.01085 -0.0891 0.2676 1.0000
10.750 1.5715 0.01702 0.01131 -0.0875 0.2612 1.0000
11.000 1.5864 0.01753 0.01183 -0.0857 0.2538 1.0000
11.250 1.6010 0.01806 0.01239 -0.0840 0.2469 1.0000
11.500 1.6146 0.01865 0.01299 -0.0821 0.2390 1.0000
11.750 1.6273 0.01931 0.01367 -0.0802 0.2312 1.0000
12.000 1.6378 0.02009 0.01446 -0.0782 0.2227 1.0000
12.250 1.6495 0.02086 0.01527 -0.0763 0.2142 1.0000
12.500 1.6560 0.02194 0.01633 -0.0741 0.2058 1.0000
12.750 1.6665 0.02286 0.01729 -0.0724 0.1969 1.0000
13.000 1.6723 0.02411 0.01854 -0.0704 0.1880 1.0000
13.250 1.6755 0.02560 0.02002 -0.0683 0.1782 1.0000
13.500 1.6798 0.02710 0.02155 -0.0665 0.1682 1.0000
13.750 1.6809 0.02893 0.02337 -0.0647 0.1588 1.0000
14.000 1.6783 0.03117 0.02560 -0.0630 0.1496 1.0000
14.250 1.6792 0.03325 0.02770 -0.0617 0.1409 1.0000
14.500 1.6763 0.03576 0.03023 -0.0604 0.1334 1.0000
14.750 1.6733 0.03842 0.03293 -0.0595 0.1264 1.0000
15.000 1.6695 0.04129 0.03583 -0.0587 0.1199 1.0000
15.250 1.6642 0.04445 0.03902 -0.0581 0.1135 1.0000
15.500 1.6586 0.04777 0.04240 -0.0578 0.1082 1.0000
15.750 1.6534 0.05119 0.04587 -0.0577 0.1026 1.0000
16.000 1.6432 0.05533 0.05005 -0.0578 0.0978 1.0000
16.250 1.6396 0.05880 0.05361 -0.0581 0.0933 1.0000
16.500 1.6293 0.06323 0.05807 -0.0587 0.0887 1.0000
16.750 1.6216 0.06745 0.06236 -0.0593 0.0850 1.0000
17.000 1.6148 0.07166 0.06664 -0.0602 0.0809 1.0000
17.250 1.6027 0.07671 0.07175 -0.0613 0.0773 1.0000
17.500 1.5952 0.08123 0.07635 -0.0625 0.0739 1.0000
17.750 1.5881 0.08576 0.08096 -0.0637 0.0706 1.0000
18.000 1.5769 0.09102 0.08626 -0.0654 0.0675 1.0000
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Polar data table (+)
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