EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 1,000,000 Max Cl/Cd: 145.06 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e434-il-1000000.txt Download as CSV file: xf-e434-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 434 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0988 0.08506 0.08269 -0.1030 0.8385 0.0083
-9.750 -0.0969 0.08194 0.07953 -0.1040 0.8273 0.0085
-9.500 -0.0951 0.07887 0.07642 -0.1050 0.8176 0.0086
-9.250 -0.0943 0.07556 0.07309 -0.1063 0.8090 0.0087
-9.000 -0.0945 0.07217 0.06967 -0.1076 0.8016 0.0089
-8.750 -0.0956 0.06864 0.06614 -0.1092 0.7943 0.0089
-8.500 -0.1005 0.06465 0.06213 -0.1111 0.7876 0.0091
-8.250 -0.1089 0.06037 0.05787 -0.1142 0.7808 0.0089
-8.000 -0.1272 0.05625 0.05370 -0.1158 0.7739 0.0089
-7.750 -0.1367 0.05254 0.04994 -0.1161 0.7687 0.0089
-7.500 -0.1421 0.04819 0.04549 -0.1164 0.7636 0.0092
-7.250 -0.1437 0.04373 0.04086 -0.1160 0.7589 0.0095
-7.000 -0.1421 0.03703 0.03386 -0.1146 0.7550 0.0099
-6.750 -0.1461 0.01764 0.01426 -0.1061 0.7440 0.0102
-6.500 -0.1362 0.01541 0.01191 -0.1052 0.7404 0.0104
-6.250 -0.1213 0.01383 0.01022 -0.1045 0.7372 0.0106
-6.000 -0.1048 0.01227 0.00852 -0.1039 0.7339 0.0108
-5.750 -0.0877 0.01062 0.00667 -0.1030 0.7307 0.0112
-5.500 -0.0694 0.00892 0.00467 -0.1020 0.7275 0.0121
-5.250 -0.0522 0.00689 0.00215 -0.1007 0.7247 0.0134
-5.000 -0.0276 0.01474 0.00908 -0.1029 0.7271 0.0076
-4.750 -0.0044 0.01279 0.00700 -0.1021 0.7241 0.0067
-4.500 0.0203 0.01166 0.00572 -0.1014 0.7212 0.0062
-4.250 0.0455 0.01090 0.00485 -0.1009 0.7180 0.0060
-4.000 0.0711 0.01036 0.00424 -0.1005 0.7148 0.0061
-3.750 0.0971 0.00998 0.00377 -0.1002 0.7116 0.0061
-3.500 0.1237 0.00962 0.00337 -0.1000 0.7086 0.0064
-3.250 0.1506 0.00931 0.00303 -0.0999 0.7055 0.0068
-3.000 0.1777 0.00906 0.00275 -0.0998 0.7024 0.0074
-2.750 0.2047 0.00878 0.00244 -0.0997 0.6992 0.0093
-2.500 0.2316 0.00853 0.00217 -0.0995 0.6958 0.0180
-2.250 0.2584 0.00823 0.00202 -0.0995 0.6929 0.0553
-2.000 0.2853 0.00795 0.00192 -0.0995 0.6896 0.1011
-1.750 0.3112 0.00751 0.00182 -0.0996 0.6863 0.2085
-1.500 0.3351 0.00677 0.00173 -0.0995 0.6829 0.4234
-1.250 0.3564 0.00582 0.00173 -0.0987 0.6793 0.7385
-1.000 0.3836 0.00577 0.00178 -0.0985 0.6761 0.7854
-0.750 0.4116 0.00579 0.00180 -0.0985 0.6725 0.8056
-0.500 0.4393 0.00583 0.00182 -0.0984 0.6688 0.8213
-0.250 0.4668 0.00590 0.00185 -0.0983 0.6649 0.8322
0.000 0.4949 0.00594 0.00188 -0.0984 0.6612 0.8417
0.250 0.5224 0.00597 0.00191 -0.0983 0.6571 0.8486
0.500 0.5504 0.00603 0.00193 -0.0984 0.6529 0.8560
0.750 0.5765 0.00612 0.00201 -0.0979 0.6486 0.8651
1.000 0.6025 0.00617 0.00209 -0.0974 0.6443 0.8760
1.250 0.6281 0.00626 0.00218 -0.0968 0.6397 0.8856
1.500 0.6547 0.00631 0.00220 -0.0966 0.6350 0.8900
1.750 0.6824 0.00633 0.00222 -0.0967 0.6304 0.8922
2.000 0.7102 0.00635 0.00224 -0.0968 0.6251 0.8942
2.250 0.7375 0.00641 0.00226 -0.0968 0.6198 0.8965
2.500 0.7656 0.00643 0.00229 -0.0970 0.6142 0.8986
2.750 0.7933 0.00648 0.00231 -0.0972 0.6080 0.9006
3.000 0.8211 0.00655 0.00236 -0.0974 0.6021 0.9025
3.250 0.8479 0.00656 0.00238 -0.0973 0.5951 0.9047
3.500 0.8740 0.00664 0.00243 -0.0971 0.5883 0.9070
3.750 0.9010 0.00668 0.00249 -0.0971 0.5808 0.9092
4.000 0.9270 0.00677 0.00257 -0.0970 0.5731 0.9116
4.250 0.9538 0.00684 0.00264 -0.0970 0.5645 0.9141
4.500 0.9801 0.00695 0.00272 -0.0969 0.5555 0.9165
4.750 1.0051 0.00706 0.00281 -0.0965 0.5448 0.9190
5.000 1.0299 0.00715 0.00291 -0.0961 0.5335 0.9218
5.250 1.0540 0.00728 0.00302 -0.0955 0.5215 0.9250
5.500 1.0778 0.00743 0.00316 -0.0950 0.5080 0.9284
5.750 1.1015 0.00762 0.00331 -0.0944 0.4931 0.9316
6.000 1.1227 0.00780 0.00346 -0.0933 0.4763 0.9354
6.250 1.1426 0.00804 0.00365 -0.0920 0.4572 0.9398
6.500 1.1620 0.00833 0.00387 -0.0906 0.4361 0.9448
6.750 1.1790 0.00860 0.00409 -0.0887 0.4147 0.9508
7.250 1.2091 0.00921 0.00459 -0.0842 0.3726 0.9711
7.500 1.2325 0.00964 0.00493 -0.0840 0.3488 0.9910
7.750 1.2503 0.01007 0.00528 -0.0827 0.3257 1.0000
8.000 1.2650 0.01059 0.00569 -0.0808 0.3036 1.0000
8.250 1.2789 0.01112 0.00613 -0.0788 0.2800 1.0000
8.500 1.2910 0.01171 0.00662 -0.0765 0.2585 1.0000
8.750 1.3043 0.01226 0.00710 -0.0744 0.2399 1.0000
9.000 1.3154 0.01291 0.00766 -0.0721 0.2202 1.0000
9.250 1.3246 0.01365 0.00832 -0.0696 0.2007 1.0000
9.500 1.3351 0.01437 0.00897 -0.0673 0.1836 1.0000
9.750 1.3450 0.01515 0.00969 -0.0651 0.1674 1.0000
10.000 1.3540 0.01602 0.01049 -0.0629 0.1513 1.0000
10.250 1.3635 0.01691 0.01133 -0.0608 0.1376 1.0000
10.500 1.3728 0.01784 0.01222 -0.0588 0.1249 1.0000
10.750 1.3814 0.01886 0.01320 -0.0569 0.1121 1.0000
11.000 1.3894 0.01995 0.01424 -0.0550 0.0999 1.0000
11.250 1.3975 0.02108 0.01534 -0.0532 0.0890 1.0000
11.500 1.4048 0.02230 0.01652 -0.0514 0.0783 1.0000
11.750 1.4116 0.02360 0.01778 -0.0496 0.0683 1.0000
12.250 1.4253 0.02630 0.02044 -0.0465 0.0519 1.0000
12.500 1.4323 0.02769 0.02183 -0.0451 0.0451 1.0000
12.750 1.4385 0.02919 0.02331 -0.0437 0.0388 1.0000
13.000 1.4433 0.03084 0.02494 -0.0423 0.0323 1.0000
13.250 1.4488 0.03248 0.02658 -0.0410 0.0280 1.0000
13.500 1.4554 0.03409 0.02821 -0.0399 0.0243 1.0000
13.750 1.4612 0.03580 0.02994 -0.0389 0.0212 1.0000
14.000 1.4674 0.03752 0.03170 -0.0380 0.0189 1.0000
14.250 1.4730 0.03934 0.03355 -0.0371 0.0165 1.0000
14.500 1.4785 0.04123 0.03547 -0.0364 0.0147 1.0000
14.750 1.4844 0.04313 0.03742 -0.0357 0.0132 1.0000
15.000 1.4893 0.04517 0.03951 -0.0351 0.0119 1.0000
15.250 1.4939 0.04729 0.04168 -0.0346 0.0107 1.0000
15.500 1.4990 0.04940 0.04386 -0.0342 0.0098 1.0000
15.750 1.5017 0.05184 0.04634 -0.0338 0.0088 1.0000
16.000 1.5061 0.05416 0.04874 -0.0336 0.0080 1.0000
16.250 1.5092 0.05665 0.05130 -0.0334 0.0072 1.0000
16.500 1.5098 0.05950 0.05421 -0.0334 0.0064 1.0000
16.750 1.5130 0.06213 0.05692 -0.0334 0.0059 1.0000
17.000 1.5139 0.06509 0.05994 -0.0336 0.0051 1.0000
17.250 1.5136 0.06827 0.06320 -0.0339 0.0046 1.0000
17.500 1.5138 0.07144 0.06646 -0.0343 0.0041 1.0000
17.750 1.5122 0.07495 0.07005 -0.0349 0.0037 1.0000
18.000 1.5084 0.07884 0.07402 -0.0357 0.0031 1.0000
18.250 1.5062 0.08260 0.07789 -0.0365 0.0028 1.0000
18.500 1.5015 0.08677 0.08214 -0.0376 0.0024 1.0000
18.750 1.4928 0.09168 0.08716 -0.0391 0.0021 1.0000
19.000 1.4886 0.09598 0.09157 -0.0404 0.0019 1.0000
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