E374 (e374-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 500,000 Max Cl/Cd: 91.4 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e374-il-500000-n5.txt Download as CSV file: xf-e374-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E374
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 -0.4962 0.07916 0.07696 -0.0377 1.0000 0.0054
-9.750 -0.5179 0.07114 0.06901 -0.0427 1.0000 0.0051
-9.000 -0.6140 0.04627 0.04391 -0.0505 1.0000 0.0048
-8.750 -0.6412 0.03530 0.03229 -0.0501 0.9880 0.0049
-8.500 -0.6346 0.02951 0.02590 -0.0504 0.9744 0.0049
-8.250 -0.6187 0.02533 0.02115 -0.0506 0.9588 0.0050
-8.000 -0.5937 0.02235 0.01770 -0.0515 0.9429 0.0050
-7.750 -0.5658 0.02007 0.01499 -0.0525 0.9248 0.0051
-7.500 -0.5400 0.01850 0.01308 -0.0526 0.9036 0.0052
-7.250 -0.5172 0.01737 0.01166 -0.0519 0.8820 0.0054
-7.000 -0.4973 0.01607 0.01008 -0.0505 0.8619 0.0056
-6.500 -0.4555 0.01427 0.00788 -0.0481 0.8291 0.0062
-6.250 -0.4326 0.01374 0.00721 -0.0473 0.8150 0.0067
-6.000 -0.4093 0.01326 0.00658 -0.0465 0.8022 0.0072
-5.750 -0.3856 0.01281 0.00601 -0.0457 0.7903 0.0076
-5.500 -0.3614 0.01242 0.00551 -0.0450 0.7793 0.0083
-5.250 -0.3367 0.01212 0.00511 -0.0445 0.7694 0.0091
-5.000 -0.3131 0.01162 0.00451 -0.0437 0.7597 0.0111
-4.750 -0.2881 0.01131 0.00411 -0.0431 0.7507 0.0130
-4.500 -0.2632 0.01099 0.00371 -0.0426 0.7425 0.0166
-4.250 -0.2377 0.01075 0.00341 -0.0421 0.7342 0.0206
-4.000 -0.2124 0.01050 0.00314 -0.0417 0.7267 0.0281
-3.750 -0.1870 0.01024 0.00290 -0.0413 0.7192 0.0409
-3.500 -0.1619 0.00996 0.00268 -0.0408 0.7124 0.0628
-3.250 -0.1366 0.00972 0.00247 -0.0404 0.7054 0.0863
-3.000 -0.1109 0.00950 0.00229 -0.0401 0.6991 0.1113
-2.750 -0.0854 0.00927 0.00214 -0.0397 0.6926 0.1428
-2.500 -0.0606 0.00898 0.00199 -0.0393 0.6866 0.1927
-2.250 -0.0366 0.00859 0.00185 -0.0388 0.6805 0.2700
-2.000 -0.0123 0.00829 0.00173 -0.0382 0.6749 0.3382
-1.750 0.0120 0.00797 0.00163 -0.0377 0.6692 0.4104
-1.500 0.0362 0.00770 0.00154 -0.0371 0.6634 0.4769
-1.250 0.0580 0.00730 0.00146 -0.0359 0.6583 0.5804
-1.000 0.0788 0.00690 0.00145 -0.0344 0.6527 0.6901
-0.750 0.1023 0.00674 0.00146 -0.0334 0.6475 0.7555
-0.500 0.1276 0.00666 0.00147 -0.0327 0.6423 0.7984
-0.250 0.1537 0.00661 0.00149 -0.0322 0.6368 0.8307
0.000 0.1803 0.00661 0.00150 -0.0318 0.6319 0.8554
0.250 0.2083 0.00660 0.00153 -0.0317 0.6265 0.8760
0.500 0.2370 0.00663 0.00157 -0.0318 0.6211 0.8954
0.750 0.2671 0.00668 0.00161 -0.0322 0.6161 0.9113
1.000 0.2994 0.00674 0.00167 -0.0331 0.6103 0.9250
1.250 0.3329 0.00683 0.00174 -0.0343 0.6049 0.9356
1.500 0.3662 0.00690 0.00181 -0.0354 0.5988 0.9452
1.750 0.3980 0.00700 0.00188 -0.0363 0.5920 0.9550
2.000 0.4334 0.00708 0.00196 -0.0379 0.5841 0.9603
2.250 0.4664 0.00718 0.00203 -0.0391 0.5755 0.9654
2.500 0.4964 0.00726 0.00209 -0.0397 0.5661 0.9706
2.750 0.5307 0.00733 0.00215 -0.0412 0.5563 0.9729
3.000 0.5634 0.00742 0.00223 -0.0424 0.5463 0.9759
3.250 0.5943 0.00752 0.00230 -0.0432 0.5349 0.9798
3.500 0.6242 0.00762 0.00239 -0.0437 0.5222 0.9835
3.750 0.6572 0.00773 0.00249 -0.0451 0.5068 0.9855
4.000 0.6895 0.00784 0.00259 -0.0462 0.4910 0.9881
4.250 0.7208 0.00799 0.00270 -0.0472 0.4720 0.9910
4.500 0.7504 0.00821 0.00285 -0.0479 0.4439 0.9940
4.750 0.7802 0.00861 0.00305 -0.0488 0.3913 0.9966
5.000 0.8064 0.00945 0.00344 -0.0493 0.2983 0.9997
5.250 0.8227 0.01009 0.00382 -0.0475 0.2414 1.0000
5.500 0.8384 0.01064 0.00417 -0.0454 0.1990 1.0000
5.750 0.8539 0.01119 0.00454 -0.0433 0.1598 1.0000
6.000 0.8694 0.01174 0.00492 -0.0413 0.1245 1.0000
6.250 0.8856 0.01224 0.00533 -0.0393 0.0976 1.0000
6.500 0.9022 0.01272 0.00571 -0.0374 0.0769 1.0000
6.750 0.9185 0.01321 0.00613 -0.0355 0.0583 1.0000
7.000 0.9346 0.01371 0.00657 -0.0335 0.0428 1.0000
7.250 0.9504 0.01423 0.00704 -0.0315 0.0299 1.0000
7.500 0.9663 0.01474 0.00752 -0.0295 0.0223 1.0000
7.750 0.9820 0.01524 0.00803 -0.0274 0.0186 1.0000
8.000 0.9978 0.01574 0.00857 -0.0254 0.0167 1.0000
8.250 1.0143 0.01619 0.00911 -0.0236 0.0157 1.0000
8.500 1.0300 0.01667 0.00965 -0.0216 0.0144 1.0000
8.750 1.0443 0.01723 0.01024 -0.0195 0.0132 1.0000
9.000 1.0553 0.01792 0.01098 -0.0168 0.0118 1.0000
9.250 1.0657 0.01850 0.01162 -0.0141 0.0111 1.0000
9.500 1.0781 0.01900 0.01220 -0.0117 0.0104 1.0000
9.750 1.0890 0.01965 0.01292 -0.0092 0.0098 1.0000
10.000 1.1002 0.02032 0.01368 -0.0070 0.0090 1.0000
10.250 1.1106 0.02108 0.01451 -0.0048 0.0085 1.0000
10.500 1.1191 0.02203 0.01550 -0.0025 0.0078 1.0000
10.750 1.1242 0.02324 0.01681 -0.0001 0.0072 1.0000
11.000 1.1357 0.02410 0.01775 0.0015 0.0067 1.0000
11.250 1.1463 0.02506 0.01880 0.0030 0.0062 1.0000
11.500 1.1576 0.02600 0.01981 0.0043 0.0056 1.0000
11.750 1.1646 0.02733 0.02122 0.0059 0.0053 1.0000
12.000 1.1754 0.02840 0.02233 0.0069 0.0048 1.0000
12.250 1.1801 0.03003 0.02406 0.0083 0.0046 1.0000
12.500 1.1826 0.03193 0.02608 0.0096 0.0044 1.0000
12.750 1.1886 0.03358 0.02786 0.0106 0.0041 1.0000
13.000 1.1908 0.03565 0.03005 0.0117 0.0040 1.0000
13.250 1.1948 0.03760 0.03212 0.0124 0.0039 1.0000
13.500 1.1992 0.03956 0.03419 0.0130 0.0037 1.0000
13.750 1.1990 0.04205 0.03682 0.0136 0.0035 1.0000
14.000 1.2014 0.04434 0.03921 0.0139 0.0034 1.0000
14.250 1.2022 0.04685 0.04185 0.0141 0.0033 1.0000
14.500 1.2007 0.04972 0.04484 0.0141 0.0032 1.0000
14.750 1.2016 0.05240 0.04763 0.0140 0.0031 1.0000
15.000 1.1944 0.05615 0.05154 0.0136 0.0031 1.0000
15.250 1.1929 0.05938 0.05488 0.0129 0.0029 1.0000
15.500 1.1866 0.06333 0.05898 0.0121 0.0030 1.0000
15.750 1.1804 0.06749 0.06326 0.0108 0.0029 1.0000
16.000 1.1715 0.07223 0.06815 0.0092 0.0029 1.0000
16.250 1.1626 0.07717 0.07323 0.0074 0.0028 1.0000
16.500 1.1517 0.08265 0.07885 0.0051 0.0028 1.0000
16.750 1.1332 0.08973 0.08608 0.0018 0.0026 1.0000
17.000 1.1237 0.09545 0.09195 -0.0009 0.0027 1.0000
17.250 1.1100 0.10220 0.09885 -0.0042 0.0027 1.0000
17.500 1.0949 0.10953 0.10631 -0.0080 0.0027 1.0000
17.750 1.0784 0.11737 0.11431 -0.0121 0.0027 1.0000
18.000 1.0584 0.12628 0.12336 -0.0168 0.0027 1.0000
18.250 1.0393 0.13533 0.13255 -0.0218 0.0027 1.0000
18.500 1.0209 0.14456 0.14191 -0.0268 0.0027 1.0000
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Polar data table (+)
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