EPPLER 403 AIRFOIL (e403-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 403 AIRFOIL (e403-il) Reynolds number: 500,000 Max Cl/Cd: 106.75 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e403-il-500000.txt Download as CSV file: xf-e403-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 403 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.2284 0.11390 0.11156 -0.0881 0.9748 0.0258
-13.000 -0.3557 0.11903 0.11658 -0.0813 0.9844 0.0229
-12.750 -0.3587 0.11615 0.11371 -0.0807 0.9815 0.0234
-12.500 -0.3584 0.11181 0.10938 -0.0826 0.9798 0.0239
-12.250 -0.3594 0.10631 0.10390 -0.0857 0.9784 0.0248
-8.500 -0.5153 0.02801 0.02232 -0.1091 0.9318 0.0171
-8.250 -0.5155 0.02792 0.02215 -0.1044 0.9261 0.0169
-8.000 -0.4998 0.02604 0.02021 -0.1024 0.9234 0.0164
-7.750 -0.4786 0.02455 0.01862 -0.1016 0.9217 0.0162
-7.500 -0.4543 0.02336 0.01734 -0.1013 0.9204 0.0162
-7.250 -0.4272 0.02238 0.01628 -0.1016 0.9193 0.0163
-7.000 -0.3986 0.02149 0.01532 -0.1024 0.9185 0.0165
-6.750 -0.3687 0.02070 0.01448 -0.1034 0.9177 0.0168
-6.500 -0.3407 0.01947 0.01321 -0.1047 0.9170 0.0173
-6.250 -0.3450 0.01916 0.01287 -0.0995 0.9095 0.0176
-6.000 -0.3181 0.01847 0.01215 -0.1003 0.9074 0.0181
-5.750 -0.2873 0.01791 0.01157 -0.1018 0.9061 0.0196
-5.500 -0.2542 0.01738 0.01100 -0.1036 0.9051 0.0207
-5.250 -0.2194 0.01679 0.01034 -0.1058 0.9044 0.0221
-5.000 -0.1838 0.01625 0.00978 -0.1080 0.9037 0.0253
-4.750 -0.1470 0.01565 0.00924 -0.1106 0.9032 0.0432
-4.500 -0.0992 0.01312 0.00805 -0.1185 0.9034 0.3489
-4.250 -0.0584 0.01235 0.00789 -0.1224 0.9031 0.5172
-4.000 -0.0225 0.01234 0.00788 -0.1242 0.9025 0.5471
-3.750 -0.0126 0.01267 0.00819 -0.1208 0.8963 0.5584
-3.500 0.0156 0.01281 0.00829 -0.1209 0.8936 0.5759
-3.250 0.0478 0.01296 0.00842 -0.1217 0.8920 0.5911
-3.000 0.0806 0.01314 0.00863 -0.1224 0.8908 0.6036
-2.750 0.1154 0.01318 0.00868 -0.1237 0.8900 0.6110
-2.500 0.1512 0.01317 0.00864 -0.1252 0.8892 0.6164
-2.250 0.1896 0.01306 0.00845 -0.1275 0.8887 0.6211
-2.000 0.2283 0.01285 0.00823 -0.1297 0.8883 0.6238
-1.750 0.2678 0.01265 0.00802 -0.1321 0.8879 0.6260
-1.500 0.2736 0.01287 0.00825 -0.1278 0.8794 0.6283
-1.250 0.3131 0.01260 0.00796 -0.1301 0.8785 0.6310
-1.000 0.3533 0.01231 0.00765 -0.1327 0.8775 0.6338
-0.750 0.3944 0.01201 0.00730 -0.1354 0.8766 0.6367
-0.500 0.4338 0.01166 0.00695 -0.1378 0.8756 0.6389
-0.250 0.4725 0.01135 0.00666 -0.1399 0.8746 0.6407
0.000 0.5108 0.01109 0.00641 -0.1420 0.8736 0.6428
0.250 0.5490 0.01084 0.00618 -0.1441 0.8725 0.6451
0.500 0.5621 0.01094 0.00631 -0.1412 0.8648 0.6477
0.750 0.5980 0.01069 0.00605 -0.1429 0.8624 0.6502
1.000 0.6359 0.01041 0.00576 -0.1450 0.8603 0.6528
1.250 0.6755 0.01005 0.00542 -0.1473 0.8582 0.6548
1.500 0.6932 0.01000 0.00543 -0.1452 0.8503 0.6567
1.750 0.7277 0.00972 0.00519 -0.1464 0.8461 0.6586
2.000 0.7582 0.00956 0.00506 -0.1469 0.8410 0.6609
2.250 0.7829 0.00944 0.00498 -0.1462 0.8333 0.6634
2.500 0.8136 0.00927 0.00482 -0.1468 0.8265 0.6660
2.750 0.8399 0.00916 0.00472 -0.1464 0.8169 0.6683
3.000 0.8640 0.00904 0.00464 -0.1456 0.8048 0.6703
3.250 0.8903 0.00893 0.00455 -0.1451 0.7898 0.6722
3.500 0.9181 0.00887 0.00448 -0.1450 0.7710 0.6744
3.750 0.9416 0.00891 0.00448 -0.1440 0.7459 0.6767
4.000 0.9650 0.00904 0.00449 -0.1430 0.7128 0.6791
4.250 0.9825 0.00932 0.00459 -0.1409 0.6712 0.6815
4.500 0.9930 0.00973 0.00478 -0.1373 0.6272 0.6838
4.750 1.0000 0.01019 0.00505 -0.1332 0.5829 0.6859
5.000 1.0046 0.01085 0.00546 -0.1287 0.5313 0.6881
5.250 1.0100 0.01158 0.00594 -0.1245 0.4775 0.6903
5.500 1.0201 0.01226 0.00639 -0.1214 0.4302 0.6926
5.750 1.0335 0.01288 0.00683 -0.1190 0.3906 0.6951
6.000 1.0490 0.01347 0.00726 -0.1170 0.3539 0.6975
6.250 1.0641 0.01413 0.00772 -0.1150 0.3135 0.6998
6.500 1.0789 0.01478 0.00820 -0.1131 0.2724 0.7020
6.750 1.0953 0.01541 0.00870 -0.1114 0.2392 0.7043
7.000 1.1113 0.01610 0.00923 -0.1097 0.2052 0.7067
7.250 1.1275 0.01681 0.00978 -0.1081 0.1712 0.7091
7.500 1.1436 0.01756 0.01037 -0.1065 0.1390 0.7116
7.750 1.1591 0.01840 0.01103 -0.1049 0.1077 0.7141
8.000 1.1734 0.01931 0.01175 -0.1031 0.0749 0.7163
8.250 1.1826 0.02061 0.01278 -0.1006 0.0362 0.7186
8.500 1.1955 0.02166 0.01376 -0.0985 0.0223 0.7210
8.750 1.2117 0.02246 0.01459 -0.0969 0.0193 0.7237
9.000 1.2271 0.02333 0.01552 -0.0953 0.0176 0.7265
9.250 1.2435 0.02414 0.01640 -0.0938 0.0167 0.7291
9.500 1.2587 0.02499 0.01734 -0.0923 0.0159 0.7315
9.750 1.2722 0.02595 0.01838 -0.0905 0.0153 0.7339
10.000 1.2829 0.02716 0.01968 -0.0884 0.0146 0.7366
10.250 1.2889 0.02875 0.02137 -0.0858 0.0141 0.7394
10.500 1.3010 0.02988 0.02259 -0.0841 0.0138 0.7425
10.750 1.3120 0.03114 0.02394 -0.0823 0.0135 0.7453
11.000 1.3228 0.03237 0.02529 -0.0805 0.0131 0.7479
11.250 1.3319 0.03378 0.02681 -0.0787 0.0128 0.7506
11.500 1.3406 0.03530 0.02844 -0.0768 0.0125 0.7535
11.750 1.3484 0.03694 0.03017 -0.0750 0.0123 0.7566
12.000 1.3562 0.03863 0.03195 -0.0734 0.0121 0.7599
12.250 1.3633 0.04041 0.03384 -0.0717 0.0119 0.7629
12.500 1.3702 0.04228 0.03583 -0.0702 0.0117 0.7660
12.750 1.3765 0.04426 0.03793 -0.0687 0.0116 0.7693
13.000 1.3825 0.04640 0.04016 -0.0673 0.0114 0.7728
13.250 1.3884 0.04867 0.04254 -0.0660 0.0112 0.7760
13.500 1.3940 0.05109 0.04509 -0.0648 0.0111 0.7791
13.750 1.3997 0.05373 0.04786 -0.0637 0.0110 0.7824
14.000 1.4054 0.05667 0.05097 -0.0626 0.0109 0.7860
14.250 1.4097 0.05986 0.05433 -0.0617 0.0108 0.7897
14.500 1.4109 0.06334 0.05803 -0.0608 0.0108 0.7931
14.750 1.4083 0.06727 0.06219 -0.0600 0.0107 0.7965
15.000 1.4022 0.07098 0.06611 -0.0595 0.0107 0.8006
15.250 1.3946 0.07501 0.07035 -0.0595 0.0107 0.8050
15.500 1.3856 0.07941 0.07497 -0.0598 0.0106 0.8089
15.750 1.3752 0.08427 0.08007 -0.0606 0.0106 0.8133
16.000 1.3637 0.08959 0.08561 -0.0619 0.0105 0.8182
16.250 1.3509 0.09537 0.09161 -0.0639 0.0105 0.8229
16.500 1.3375 0.10147 0.09793 -0.0664 0.0105 0.8282
16.750 1.3228 0.10815 0.10483 -0.0695 0.0105 0.8341
17.000 1.3051 0.11575 0.11265 -0.0733 0.0106 0.8394
17.250 1.2888 0.12337 0.12048 -0.0778 0.0105 0.8467
17.500 1.2718 0.13148 0.12880 -0.0828 0.0106 0.8545
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