E374 (e374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.74 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e374-il-1000000.txt Download as CSV file: xf-e374-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4554 0.08413 0.08256 -0.0362 1.0000 0.0111
-9.500 -0.4618 0.07839 0.07685 -0.0391 1.0000 0.0112
-9.250 -0.4673 0.07257 0.07105 -0.0427 1.0000 0.0112
-9.000 -0.4824 0.06308 0.06158 -0.0517 1.0000 0.0111
-7.750 -0.5737 0.02165 0.01793 -0.0514 0.9685 0.0069
-7.500 -0.5509 0.01798 0.01373 -0.0515 0.9531 0.0066
-7.250 -0.5234 0.01582 0.01122 -0.0519 0.9326 0.0066
-7.000 -0.4996 0.01462 0.00976 -0.0512 0.9072 0.0068
-6.750 -0.4779 0.01377 0.00867 -0.0500 0.8838 0.0071
-6.500 -0.4539 0.01346 0.00821 -0.0492 0.8633 0.0076
-6.250 -0.4315 0.01284 0.00742 -0.0481 0.8451 0.0077
-6.000 -0.4134 0.01153 0.00589 -0.0463 0.8289 0.0083
-5.750 -0.3905 0.01102 0.00525 -0.0454 0.8144 0.0087
-5.500 -0.3662 0.01068 0.00483 -0.0447 0.8012 0.0093
-5.250 -0.3417 0.01033 0.00439 -0.0441 0.7891 0.0099
-5.000 -0.3166 0.01006 0.00403 -0.0435 0.7782 0.0107
-4.750 -0.2924 0.00965 0.00351 -0.0428 0.7680 0.0122
-4.500 -0.2673 0.00935 0.00315 -0.0422 0.7582 0.0143
-4.250 -0.2421 0.00902 0.00277 -0.0417 0.7493 0.0186
-4.000 -0.2167 0.00878 0.00249 -0.0412 0.7410 0.0259
-3.750 -0.1911 0.00852 0.00226 -0.0408 0.7327 0.0384
-3.500 -0.1657 0.00827 0.00208 -0.0404 0.7254 0.0611
-3.250 -0.1401 0.00802 0.00191 -0.0400 0.7179 0.0899
-3.000 -0.1150 0.00775 0.00175 -0.0396 0.7112 0.1309
-2.750 -0.0899 0.00746 0.00162 -0.0392 0.7045 0.1825
-2.500 -0.0652 0.00717 0.00150 -0.0387 0.6983 0.2420
-2.250 -0.0403 0.00686 0.00139 -0.0383 0.6919 0.3104
-2.000 -0.0163 0.00654 0.00129 -0.0377 0.6859 0.3919
-1.750 0.0057 0.00603 0.00120 -0.0367 0.6802 0.5193
-1.500 0.0281 0.00565 0.00114 -0.0357 0.6743 0.6213
-1.250 0.0506 0.00537 0.00111 -0.0346 0.6689 0.7113
-1.000 0.0748 0.00521 0.00111 -0.0337 0.6633 0.7701
-0.750 0.1000 0.00514 0.00111 -0.0330 0.6578 0.8089
-0.500 0.1259 0.00509 0.00113 -0.0325 0.6526 0.8414
-0.250 0.1524 0.00506 0.00113 -0.0321 0.6471 0.8635
0.000 0.1789 0.00507 0.00115 -0.0317 0.6419 0.8825
0.250 0.2063 0.00506 0.00117 -0.0315 0.6366 0.9003
0.500 0.2340 0.00508 0.00120 -0.0314 0.6311 0.9157
0.750 0.2625 0.00513 0.00124 -0.0315 0.6258 0.9293
1.000 0.2919 0.00517 0.00129 -0.0317 0.6197 0.9412
1.250 0.3236 0.00527 0.00135 -0.0325 0.6134 0.9500
1.500 0.3541 0.00532 0.00141 -0.0330 0.6064 0.9582
1.750 0.3872 0.00544 0.00148 -0.0342 0.5992 0.9642
2.000 0.4172 0.00551 0.00155 -0.0346 0.5917 0.9709
2.250 0.4556 0.00562 0.00163 -0.0370 0.5840 0.9731
2.500 0.4941 0.00570 0.00170 -0.0394 0.5757 0.9756
2.750 0.5298 0.00580 0.00178 -0.0412 0.5674 0.9791
3.000 0.5607 0.00590 0.00187 -0.0419 0.5582 0.9835
3.250 0.5974 0.00596 0.00191 -0.0440 0.5476 0.9848
3.500 0.6329 0.00603 0.00197 -0.0458 0.5370 0.9863
3.750 0.6675 0.00611 0.00204 -0.0474 0.5256 0.9882
4.000 0.7009 0.00621 0.00211 -0.0488 0.5091 0.9904
4.250 0.7327 0.00638 0.00220 -0.0499 0.4834 0.9930
4.500 0.7652 0.00654 0.00230 -0.0512 0.4609 0.9948
4.750 0.7983 0.00678 0.00242 -0.0526 0.4238 0.9965
5.000 0.8290 0.00727 0.00263 -0.0538 0.3586 0.9986
5.250 0.8549 0.00790 0.00293 -0.0541 0.2877 1.0000
5.500 0.8706 0.00841 0.00324 -0.0520 0.2384 1.0000
6.000 0.9016 0.00946 0.00389 -0.0478 0.1534 1.0000
6.250 0.9174 0.00997 0.00423 -0.0457 0.1191 1.0000
6.500 0.9322 0.01053 0.00462 -0.0434 0.0862 1.0000
6.750 0.9474 0.01106 0.00501 -0.0412 0.0591 1.0000
7.000 0.9608 0.01170 0.00551 -0.0387 0.0321 1.0000
7.250 0.9757 0.01226 0.00598 -0.0363 0.0207 1.0000
7.500 0.9935 0.01263 0.00639 -0.0346 0.0181 1.0000
7.750 1.0107 0.01304 0.00682 -0.0327 0.0163 1.0000
8.000 1.0251 0.01362 0.00745 -0.0303 0.0141 1.0000
8.250 1.0418 0.01405 0.00793 -0.0284 0.0133 1.0000
8.500 1.0588 0.01445 0.00839 -0.0265 0.0125 1.0000
8.750 1.0750 0.01489 0.00886 -0.0246 0.0116 1.0000
9.000 1.0897 0.01540 0.00940 -0.0224 0.0106 1.0000
9.250 1.0949 0.01642 0.01052 -0.0187 0.0095 1.0000
9.500 1.1062 0.01694 0.01111 -0.0159 0.0090 1.0000
9.750 1.1206 0.01728 0.01147 -0.0137 0.0085 1.0000
10.000 1.1304 0.01788 0.01213 -0.0109 0.0080 1.0000
10.250 1.1445 0.01832 0.01259 -0.0089 0.0074 1.0000
10.500 1.1551 0.01900 0.01332 -0.0066 0.0069 1.0000
10.750 1.1598 0.02006 0.01445 -0.0036 0.0065 1.0000
11.000 1.1579 0.02165 0.01617 0.0000 0.0061 1.0000
11.250 1.1692 0.02248 0.01707 0.0017 0.0059 1.0000
11.500 1.1769 0.02361 0.01828 0.0036 0.0057 1.0000
11.750 1.1891 0.02446 0.01920 0.0049 0.0053 1.0000
12.000 1.1965 0.02573 0.02055 0.0065 0.0052 1.0000
12.250 1.2040 0.02705 0.02195 0.0079 0.0050 1.0000
12.500 1.2098 0.02857 0.02355 0.0093 0.0048 1.0000
12.750 1.2190 0.02984 0.02488 0.0103 0.0046 1.0000
13.000 1.2261 0.03133 0.02645 0.0112 0.0045 1.0000
13.250 1.2296 0.03320 0.02840 0.0122 0.0043 1.0000
13.500 1.2297 0.03548 0.03081 0.0132 0.0043 1.0000
13.750 1.2258 0.03822 0.03367 0.0142 0.0042 1.0000
14.000 1.2068 0.04267 0.03834 0.0156 0.0040 1.0000
14.250 1.2020 0.04574 0.04156 0.0161 0.0039 1.0000
14.500 1.2013 0.04849 0.04443 0.0162 0.0039 1.0000
14.750 1.1981 0.05161 0.04768 0.0161 0.0039 1.0000
15.000 1.1997 0.05429 0.05047 0.0157 0.0038 1.0000
15.250 1.1909 0.05835 0.05468 0.0152 0.0038 1.0000
15.500 1.1785 0.06306 0.05955 0.0142 0.0038 1.0000
15.750 1.1815 0.06599 0.06258 0.0131 0.0035 1.0000
16.000 1.1643 0.07184 0.06860 0.0114 0.0036 1.0000
16.250 1.1545 0.07691 0.07381 0.0094 0.0036 1.0000
16.500 1.1433 0.08245 0.07949 0.0071 0.0035 1.0000
16.750 1.1287 0.08886 0.08605 0.0042 0.0034 1.0000
17.000 1.1107 0.09605 0.09338 0.0007 0.0036 1.0000
17.250 1.0888 0.10454 0.10205 -0.0036 0.0035 1.0000
17.500 1.0675 0.11326 0.11091 -0.0082 0.0036 1.0000
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Polar data table (+)
Polar graphs
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