EPPLER 434 AIRFOIL (e434-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: EPPLER 434 AIRFOIL (e434-il) Reynolds number: 500,000 Max Cl/Cd: 109.22 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e434-il-500000-n5.txt Download as CSV file: xf-e434-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1181 0.08469 0.08156 -0.1008 0.8204 0.0100
-9.750 -0.1165 0.08114 0.07799 -0.1021 0.8123 0.0100
-9.500 -0.1153 0.07767 0.07449 -0.1034 0.8044 0.0100
-9.250 -0.0783 0.06391 0.06080 -0.0946 0.7766 0.0074
-9.000 -0.0774 0.06076 0.05763 -0.0957 0.7723 0.0072
-8.750 -0.0789 0.05692 0.05381 -0.0971 0.7682 0.0071
-8.500 -0.0839 0.05260 0.04949 -0.0990 0.7640 0.0068
-8.250 -0.0908 0.04814 0.04503 -0.1013 0.7600 0.0067
-8.000 -0.1083 0.04270 0.03958 -0.1059 0.7560 0.0065
-7.750 -0.1814 0.04580 0.04232 -0.1137 0.7603 0.0056
-7.500 -0.1835 0.04107 0.03738 -0.1129 0.7561 0.0053
-7.250 -0.1828 0.03686 0.03296 -0.1117 0.7518 0.0052
-7.000 -0.1786 0.03274 0.02856 -0.1102 0.7475 0.0050
-6.750 -0.1754 0.02773 0.02312 -0.1079 0.7436 0.0049
-6.500 -0.1677 0.02327 0.01811 -0.1056 0.7404 0.0047
-6.250 -0.1525 0.02014 0.01449 -0.1039 0.7369 0.0046
-6.000 -0.1325 0.01808 0.01202 -0.1027 0.7333 0.0046
-5.750 -0.1100 0.01658 0.01020 -0.1018 0.7299 0.0046
-5.500 -0.0862 0.01550 0.00888 -0.1012 0.7269 0.0046
-5.250 -0.0618 0.01457 0.00778 -0.1006 0.7239 0.0047
-5.000 -0.0368 0.01386 0.00694 -0.1002 0.7206 0.0047
-4.750 -0.0119 0.01319 0.00616 -0.0997 0.7171 0.0049
-4.500 0.0134 0.01269 0.00556 -0.0993 0.7139 0.0050
-4.250 0.0390 0.01225 0.00502 -0.0990 0.7111 0.0052
-4.000 0.0645 0.01178 0.00449 -0.0987 0.7080 0.0057
-3.750 0.0908 0.01145 0.00414 -0.0985 0.7046 0.0060
-3.500 0.1173 0.01118 0.00382 -0.0983 0.7013 0.0069
-3.250 0.1440 0.01094 0.00351 -0.0982 0.6982 0.0077
-3.000 0.1706 0.01071 0.00323 -0.0980 0.6953 0.0091
-2.750 0.1975 0.01049 0.00302 -0.0980 0.6921 0.0129
-2.500 0.2240 0.01020 0.00281 -0.0978 0.6887 0.0276
-2.250 0.2503 0.00993 0.00265 -0.0978 0.6852 0.0596
-2.000 0.2766 0.00966 0.00253 -0.0977 0.6820 0.1069
-1.750 0.3022 0.00927 0.00241 -0.0976 0.6790 0.1952
-1.500 0.3274 0.00879 0.00233 -0.0976 0.6754 0.3174
-1.250 0.3522 0.00826 0.00224 -0.0975 0.6718 0.4625
-1.000 0.3742 0.00753 0.00221 -0.0967 0.6682 0.6766
-0.750 0.3986 0.00746 0.00234 -0.0958 0.6650 0.7726
-0.500 0.4252 0.00749 0.00240 -0.0954 0.6613 0.8004
-0.250 0.4522 0.00753 0.00243 -0.0952 0.6572 0.8167
0.000 0.4791 0.00759 0.00246 -0.0950 0.6531 0.8297
0.250 0.5044 0.00769 0.00254 -0.0942 0.6494 0.8489
0.500 0.5285 0.00779 0.00267 -0.0932 0.6450 0.8677
0.750 0.5534 0.00786 0.00273 -0.0925 0.6403 0.8773
1.000 0.5806 0.00790 0.00273 -0.0924 0.6358 0.8805
1.250 0.6084 0.00794 0.00273 -0.0925 0.6310 0.8829
1.500 0.6362 0.00797 0.00274 -0.0927 0.6256 0.8855
1.750 0.6637 0.00803 0.00274 -0.0928 0.6204 0.8878
2.000 0.6907 0.00806 0.00277 -0.0927 0.6149 0.8895
2.250 0.7175 0.00810 0.00281 -0.0926 0.6089 0.8915
2.500 0.7440 0.00817 0.00284 -0.0925 0.6032 0.8939
2.750 0.7708 0.00822 0.00289 -0.0925 0.5965 0.8964
3.000 0.7973 0.00829 0.00294 -0.0924 0.5897 0.8989
3.250 0.8243 0.00836 0.00301 -0.0924 0.5822 0.9013
3.750 0.8754 0.00852 0.00315 -0.0918 0.5655 0.9058
4.000 0.9001 0.00862 0.00323 -0.0913 0.5566 0.9085
4.250 0.9247 0.00873 0.00335 -0.0909 0.5463 0.9117
4.500 0.9496 0.00885 0.00346 -0.0905 0.5359 0.9148
4.750 0.9739 0.00900 0.00358 -0.0900 0.5246 0.9177
5.000 0.9961 0.00914 0.00372 -0.0891 0.5120 0.9208
5.250 1.0179 0.00932 0.00387 -0.0881 0.4983 0.9244
5.500 1.0392 0.00952 0.00405 -0.0871 0.4826 0.9284
5.750 1.0597 0.00975 0.00425 -0.0859 0.4657 0.9327
6.000 1.0775 0.00999 0.00446 -0.0841 0.4476 0.9382
6.250 1.0948 0.01028 0.00469 -0.0823 0.4291 0.9449
6.500 1.1101 0.01059 0.00496 -0.0802 0.4099 0.9530
6.750 1.1265 0.01093 0.00525 -0.0783 0.3899 0.9640
7.000 1.1473 0.01138 0.00563 -0.0776 0.3667 0.9818
7.250 1.1634 0.01186 0.00603 -0.0760 0.3450 1.0000
7.500 1.1773 0.01238 0.00648 -0.0741 0.3238 1.0000
7.750 1.1900 0.01297 0.00698 -0.0719 0.3036 1.0000
8.000 1.2038 0.01353 0.00749 -0.0700 0.2859 1.0000
8.250 1.2167 0.01414 0.00805 -0.0680 0.2681 1.0000
8.500 1.2275 0.01487 0.00870 -0.0658 0.2484 1.0000
8.750 1.2383 0.01562 0.00939 -0.0637 0.2312 1.0000
9.000 1.2489 0.01642 0.01014 -0.0617 0.2143 1.0000
9.250 1.2585 0.01731 0.01097 -0.0597 0.1959 1.0000
9.500 1.2678 0.01826 0.01186 -0.0577 0.1789 1.0000
9.750 1.2781 0.01919 0.01276 -0.0559 0.1652 1.0000
10.000 1.2874 0.02023 0.01376 -0.0541 0.1505 1.0000
10.250 1.2960 0.02134 0.01482 -0.0524 0.1363 1.0000
10.500 1.3043 0.02251 0.01595 -0.0507 0.1224 1.0000
10.750 1.3128 0.02371 0.01712 -0.0491 0.1101 1.0000
11.000 1.3214 0.02493 0.01833 -0.0476 0.0996 1.0000
11.250 1.3296 0.02622 0.01960 -0.0462 0.0897 1.0000
11.500 1.3371 0.02759 0.02095 -0.0448 0.0800 1.0000
11.750 1.3452 0.02895 0.02232 -0.0435 0.0716 1.0000
12.000 1.3533 0.03035 0.02373 -0.0423 0.0645 1.0000
12.250 1.3601 0.03187 0.02525 -0.0410 0.0574 1.0000
12.500 1.3666 0.03346 0.02685 -0.0399 0.0507 1.0000
12.750 1.3738 0.03504 0.02846 -0.0388 0.0451 1.0000
13.000 1.3794 0.03679 0.03022 -0.0378 0.0398 1.0000
13.250 1.3856 0.03854 0.03200 -0.0369 0.0351 1.0000
13.500 1.3912 0.04039 0.03389 -0.0360 0.0311 1.0000
13.750 1.3959 0.04237 0.03590 -0.0353 0.0275 1.0000
14.000 1.4019 0.04429 0.03788 -0.0346 0.0248 1.0000
14.250 1.4058 0.04645 0.04009 -0.0340 0.0223 1.0000
14.500 1.4114 0.04851 0.04222 -0.0335 0.0202 1.0000
14.750 1.4148 0.05084 0.04460 -0.0331 0.0182 1.0000
15.000 1.4188 0.05318 0.04702 -0.0327 0.0165 1.0000
15.250 1.4220 0.05566 0.04955 -0.0325 0.0148 1.0000
15.500 1.4247 0.05824 0.05220 -0.0324 0.0133 1.0000
15.750 1.4272 0.06091 0.05497 -0.0324 0.0121 1.0000
16.000 1.4280 0.06387 0.05798 -0.0325 0.0106 1.0000
16.250 1.4300 0.06673 0.06095 -0.0327 0.0098 1.0000
16.500 1.4299 0.06992 0.06420 -0.0330 0.0087 1.0000
16.750 1.4304 0.07312 0.06750 -0.0334 0.0079 1.0000
17.000 1.4300 0.07651 0.07099 -0.0340 0.0071 1.0000
17.250 1.4283 0.08015 0.07473 -0.0348 0.0066 1.0000
17.500 1.4267 0.08386 0.07854 -0.0356 0.0061 1.0000
17.750 1.4245 0.08772 0.08251 -0.0366 0.0055 1.0000
18.000 1.4207 0.09189 0.08677 -0.0379 0.0049 1.0000
18.250 1.4165 0.09624 0.09124 -0.0392 0.0046 1.0000
18.500 1.4130 0.10052 0.09564 -0.0407 0.0042 1.0000
18.750 1.4081 0.10511 0.10035 -0.0424 0.0039 1.0000
19.000 1.4017 0.10999 0.10533 -0.0444 0.0035 1.0000
19.250 1.3949 0.11504 0.11049 -0.0465 0.0032 1.0000
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Polar data table (+)
Polar graphs
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