EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 200,000 Max Cl/Cd: 87.54 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e393-il-200000.txt Download as CSV file: xf-e393-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3239 0.09280 0.08963 -0.0418 1.0000 0.0466
-8.250 -0.3332 0.09083 0.08775 -0.0401 1.0000 0.0477
-8.000 -0.3493 0.08954 0.08657 -0.0372 1.0000 0.0481
-7.750 -0.3438 0.08566 0.08272 -0.0417 0.9961 0.0499
-7.500 -0.3242 0.07304 0.07004 -0.0727 0.9784 0.0533
-7.250 -0.3092 0.06369 0.06061 -0.0831 0.9711 0.0546
-7.000 -0.2865 0.06189 0.05890 -0.0817 0.9652 0.0562
-6.750 -0.2592 0.05734 0.05428 -0.0880 0.9586 0.0589
-6.250 -0.1564 0.02709 0.02366 -0.1084 0.9263 0.0724
-6.000 -0.1741 0.02801 0.02238 -0.1142 0.9317 0.0314
-5.750 -0.1418 0.02437 0.01828 -0.1164 0.9248 0.0320
-5.500 -0.1073 0.02244 0.01621 -0.1185 0.9184 0.0350
-5.250 -0.0729 0.02007 0.01342 -0.1198 0.9113 0.0355
-5.000 -0.0386 0.01831 0.01139 -0.1208 0.9039 0.0373
-4.750 -0.0068 0.01701 0.00989 -0.1213 0.8949 0.0404
-4.500 0.0262 0.01561 0.00844 -0.1224 0.8876 0.0479
-4.250 0.0546 0.01462 0.00738 -0.1224 0.8766 0.0570
-4.000 0.0838 0.01386 0.00659 -0.1228 0.8667 0.0718
-3.750 0.1143 0.01300 0.00578 -0.1234 0.8581 0.1048
-3.500 0.1419 0.01203 0.00520 -0.1239 0.8474 0.1967
-3.250 0.1692 0.01128 0.00497 -0.1244 0.8377 0.3450
-3.000 0.1974 0.01099 0.00495 -0.1244 0.8294 0.4624
-2.750 0.2243 0.01097 0.00495 -0.1241 0.8196 0.5255
-2.500 0.2514 0.01099 0.00495 -0.1237 0.8109 0.5647
-2.250 0.2792 0.01100 0.00490 -0.1234 0.8030 0.5965
-2.000 0.3056 0.01104 0.00492 -0.1229 0.7941 0.6247
-1.750 0.3332 0.01106 0.00487 -0.1226 0.7873 0.6508
-1.500 0.3591 0.01110 0.00491 -0.1220 0.7786 0.6746
-1.250 0.3864 0.01113 0.00489 -0.1216 0.7719 0.6981
-1.000 0.4120 0.01115 0.00493 -0.1210 0.7640 0.7201
-0.750 0.4390 0.01119 0.00492 -0.1206 0.7576 0.7434
-0.500 0.4637 0.01121 0.00498 -0.1198 0.7500 0.7651
-0.250 0.4899 0.01124 0.00498 -0.1192 0.7442 0.7890
0.000 0.5134 0.01126 0.00506 -0.1181 0.7366 0.8140
0.250 0.5373 0.01126 0.00505 -0.1169 0.7310 0.8404
0.500 0.5576 0.01126 0.00513 -0.1151 0.7238 0.8709
0.750 0.5781 0.01119 0.00508 -0.1131 0.7181 0.9082
1.000 0.6082 0.01110 0.00502 -0.1135 0.7116 0.9661
1.250 0.6446 0.01120 0.00502 -0.1157 0.7052 1.0000
1.500 0.6755 0.01138 0.00512 -0.1167 0.6993 1.0000
1.750 0.7047 0.01155 0.00524 -0.1173 0.6925 1.0000
2.000 0.7351 0.01173 0.00531 -0.1179 0.6875 1.0000
2.250 0.7623 0.01192 0.00553 -0.1180 0.6802 1.0000
2.500 0.7917 0.01209 0.00564 -0.1184 0.6746 1.0000
2.750 0.8189 0.01230 0.00586 -0.1185 0.6677 1.0000
3.000 0.8474 0.01246 0.00599 -0.1187 0.6615 1.0000
3.250 0.8747 0.01265 0.00619 -0.1187 0.6546 1.0000
3.500 0.9026 0.01280 0.00634 -0.1187 0.6474 1.0000
3.750 0.9296 0.01298 0.00654 -0.1186 0.6399 1.0000
4.000 0.9575 0.01311 0.00666 -0.1186 0.6327 1.0000
4.250 0.9838 0.01328 0.00688 -0.1184 0.6244 1.0000
4.500 1.0121 0.01339 0.00697 -0.1184 0.6169 1.0000
4.750 1.0373 0.01354 0.00721 -0.1179 0.6075 1.0000
5.000 1.0643 0.01366 0.00734 -0.1177 0.5990 1.0000
5.250 1.0908 0.01374 0.00745 -0.1174 0.5893 1.0000
5.500 1.1158 0.01385 0.00768 -0.1168 0.5788 1.0000
5.750 1.1415 0.01396 0.00783 -0.1163 0.5685 1.0000
6.000 1.1671 0.01404 0.00795 -0.1158 0.5574 1.0000
6.250 1.1920 0.01411 0.00806 -0.1152 0.5448 1.0000
6.500 1.2159 0.01421 0.00823 -0.1144 0.5312 1.0000
6.750 1.2391 0.01434 0.00846 -0.1134 0.5161 1.0000
7.000 1.2611 0.01447 0.00871 -0.1123 0.4978 1.0000
7.250 1.2825 0.01465 0.00892 -0.1110 0.4766 1.0000
7.500 1.3023 0.01490 0.00920 -0.1096 0.4506 1.0000
7.750 1.3199 0.01529 0.00954 -0.1077 0.4181 1.0000
8.000 1.3345 0.01587 0.01004 -0.1055 0.3759 1.0000
8.250 1.3437 0.01679 0.01071 -0.1025 0.3226 1.0000
8.500 1.3470 0.01808 0.01167 -0.0988 0.2665 1.0000
8.750 1.3470 0.01951 0.01279 -0.0948 0.2155 1.0000
9.000 1.3451 0.02096 0.01396 -0.0906 0.1735 1.0000
9.250 1.3442 0.02247 0.01523 -0.0869 0.1392 1.0000
9.500 1.3456 0.02395 0.01657 -0.0837 0.1129 1.0000
9.750 1.3482 0.02547 0.01800 -0.0808 0.0915 1.0000
10.000 1.3492 0.02719 0.01965 -0.0781 0.0725 1.0000
10.250 1.3463 0.02934 0.02169 -0.0752 0.0539 1.0000
10.500 1.3386 0.03209 0.02439 -0.0723 0.0378 1.0000
10.750 1.3300 0.03512 0.02743 -0.0697 0.0303 1.0000
11.000 1.3295 0.03760 0.03005 -0.0679 0.0263 1.0000
11.250 1.3239 0.04069 0.03318 -0.0663 0.0238 1.0000
11.500 1.3218 0.04359 0.03619 -0.0648 0.0221 1.0000
11.750 1.3262 0.04590 0.03864 -0.0639 0.0204 1.0000
12.000 1.3295 0.04838 0.04122 -0.0630 0.0190 1.0000
12.250 1.3320 0.05102 0.04395 -0.0621 0.0181 1.0000
12.500 1.3344 0.05379 0.04679 -0.0613 0.0174 1.0000
12.750 1.3382 0.05660 0.04968 -0.0602 0.0167 1.0000
13.000 1.3495 0.05954 0.05272 -0.0583 0.0160 1.0000
13.250 1.3567 0.06223 0.05562 -0.0576 0.0158 1.0000
13.500 1.3624 0.06523 0.05883 -0.0569 0.0156 1.0000
13.750 1.3657 0.06862 0.06246 -0.0564 0.0155 1.0000
14.000 1.3654 0.07248 0.06658 -0.0562 0.0154 1.0000
14.250 1.3616 0.07679 0.07115 -0.0562 0.0154 1.0000
14.500 1.3545 0.08156 0.07622 -0.0566 0.0154 1.0000
14.750 1.3447 0.08679 0.08171 -0.0575 0.0154 1.0000
15.000 1.3324 0.09247 0.08764 -0.0589 0.0155 1.0000
15.250 1.3183 0.09858 0.09400 -0.0609 0.0156 1.0000
15.500 1.3026 0.10517 0.10082 -0.0634 0.0157 1.0000
15.750 1.2859 0.11222 0.10810 -0.0666 0.0158 1.0000
16.000 1.2683 0.11977 0.11585 -0.0703 0.0159 1.0000
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Polar data table (+)
Polar graphs
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