E374 (e374-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: E374 (e374-il) Reynolds number: 1,000,000 Max Cl/Cd: 99.86 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e374-il-1000000-n5.txt Download as CSV file: xf-e374-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.7627 0.03917 0.03717 -0.0571 1.0000 0.0027
-10.500 -0.7781 0.03629 0.03412 -0.0532 1.0000 0.0027
-10.250 -0.7973 0.03105 0.02846 -0.0499 0.9979 0.0027
-9.750 -0.7725 0.02406 0.02067 -0.0502 0.9827 0.0028
-9.500 -0.7492 0.02238 0.01876 -0.0507 0.9721 0.0029
-9.250 -0.7206 0.02061 0.01672 -0.0522 0.9572 0.0029
-9.000 -0.6902 0.01883 0.01464 -0.0539 0.9325 0.0029
-8.750 -0.6661 0.01805 0.01363 -0.0537 0.9010 0.0030
-8.500 -0.6443 0.01763 0.01304 -0.0527 0.8742 0.0031
-8.250 -0.6266 0.01655 0.01169 -0.0512 0.8512 0.0031
-8.000 -0.6093 0.01531 0.01016 -0.0495 0.8321 0.0032
-7.750 -0.5901 0.01430 0.00892 -0.0481 0.8157 0.0034
-7.500 -0.5687 0.01359 0.00803 -0.0470 0.8010 0.0035
-7.000 -0.5223 0.01260 0.00680 -0.0455 0.7759 0.0040
-6.750 -0.4987 0.01212 0.00620 -0.0448 0.7651 0.0040
-6.500 -0.4744 0.01175 0.00573 -0.0442 0.7547 0.0043
-6.000 -0.4250 0.01104 0.00483 -0.0431 0.7360 0.0049
-5.750 -0.3999 0.01074 0.00445 -0.0427 0.7278 0.0051
-5.500 -0.3745 0.01046 0.00408 -0.0422 0.7195 0.0053
-5.250 -0.3491 0.01017 0.00373 -0.0418 0.7123 0.0056
-5.000 -0.3239 0.00985 0.00332 -0.0413 0.7048 0.0066
-4.750 -0.2980 0.00962 0.00306 -0.0409 0.6982 0.0078
-4.500 -0.2720 0.00941 0.00280 -0.0406 0.6914 0.0097
-4.250 -0.2459 0.00921 0.00258 -0.0403 0.6851 0.0134
-4.000 -0.2197 0.00903 0.00238 -0.0400 0.6788 0.0175
-3.750 -0.1933 0.00887 0.00220 -0.0398 0.6731 0.0220
-3.500 -0.1668 0.00870 0.00204 -0.0396 0.6671 0.0283
-3.250 -0.1408 0.00851 0.00187 -0.0393 0.6615 0.0431
-3.000 -0.1147 0.00829 0.00172 -0.0390 0.6563 0.0653
-2.750 -0.0886 0.00809 0.00159 -0.0388 0.6506 0.0891
-2.500 -0.0624 0.00794 0.00148 -0.0385 0.6456 0.1112
-2.250 -0.0359 0.00776 0.00137 -0.0383 0.6406 0.1373
-2.000 -0.0100 0.00756 0.00127 -0.0380 0.6353 0.1775
-1.750 0.0151 0.00727 0.00119 -0.0376 0.6304 0.2423
-1.250 0.0663 0.00683 0.00104 -0.0370 0.6202 0.3517
-1.000 0.0924 0.00666 0.00099 -0.0367 0.6155 0.3979
-0.750 0.1168 0.00635 0.00094 -0.0362 0.6104 0.4825
-0.500 0.1406 0.00605 0.00090 -0.0355 0.6055 0.5729
-0.250 0.1644 0.00578 0.00088 -0.0348 0.6007 0.6541
0.000 0.1886 0.00558 0.00088 -0.0340 0.5955 0.7204
0.250 0.2134 0.00548 0.00090 -0.0333 0.5904 0.7697
0.500 0.2395 0.00541 0.00092 -0.0329 0.5852 0.8017
0.750 0.2659 0.00539 0.00094 -0.0326 0.5794 0.8257
1.000 0.2923 0.00537 0.00097 -0.0322 0.5736 0.8474
1.250 0.3189 0.00537 0.00100 -0.0319 0.5661 0.8674
1.750 0.3727 0.00541 0.00109 -0.0315 0.5492 0.9032
2.000 0.4011 0.00545 0.00115 -0.0315 0.5400 0.9195
2.250 0.4311 0.00552 0.00124 -0.0320 0.5304 0.9349
2.500 0.4633 0.00563 0.00133 -0.0330 0.5199 0.9481
2.750 0.4947 0.00573 0.00141 -0.0338 0.5090 0.9578
3.000 0.5268 0.00585 0.00150 -0.0348 0.4956 0.9636
3.250 0.5540 0.00597 0.00159 -0.0347 0.4816 0.9701
3.750 0.6181 0.00628 0.00179 -0.0369 0.4462 0.9750
4.000 0.6481 0.00649 0.00192 -0.0376 0.4232 0.9781
4.250 0.6731 0.00678 0.00209 -0.0372 0.3867 0.9829
4.500 0.7009 0.00753 0.00242 -0.0379 0.2977 0.9847
4.750 0.7278 0.00829 0.00280 -0.0385 0.2166 0.9872
5.000 0.7567 0.00873 0.00308 -0.0392 0.1782 0.9897
5.250 0.7847 0.00914 0.00336 -0.0396 0.1476 0.9923
5.500 0.8124 0.00957 0.00365 -0.0401 0.1181 0.9945
5.750 0.8415 0.01006 0.00398 -0.0409 0.0848 0.9963
6.000 0.8710 0.01047 0.00430 -0.0417 0.0641 0.9982
6.250 0.9001 0.01093 0.00467 -0.0425 0.0440 0.9997
6.500 0.9202 0.01131 0.00499 -0.0413 0.0316 1.0000
6.750 0.9373 0.01172 0.00534 -0.0394 0.0210 1.0000
7.000 0.9555 0.01206 0.00567 -0.0377 0.0163 1.0000
7.250 0.9743 0.01237 0.00600 -0.0361 0.0148 1.0000
7.500 0.9922 0.01273 0.00636 -0.0344 0.0129 1.0000
7.750 1.0099 0.01310 0.00676 -0.0326 0.0113 1.0000
8.000 1.0289 0.01340 0.00711 -0.0311 0.0109 1.0000
8.250 1.0474 0.01372 0.00747 -0.0295 0.0104 1.0000
8.500 1.0654 0.01407 0.00786 -0.0279 0.0098 1.0000
8.750 1.0828 0.01445 0.00827 -0.0261 0.0092 1.0000
9.000 1.0994 0.01486 0.00870 -0.0243 0.0085 1.0000
9.250 1.1146 0.01534 0.00921 -0.0223 0.0076 1.0000
9.500 1.1315 0.01572 0.00962 -0.0206 0.0070 1.0000
9.750 1.1473 0.01612 0.01008 -0.0187 0.0066 1.0000
10.000 1.1608 0.01651 0.01050 -0.0164 0.0058 1.0000
10.250 1.1730 0.01696 0.01097 -0.0139 0.0053 1.0000
10.500 1.1844 0.01749 0.01153 -0.0114 0.0046 1.0000
10.750 1.1962 0.01807 0.01216 -0.0091 0.0043 1.0000
11.000 1.2082 0.01868 0.01282 -0.0070 0.0039 1.0000
11.250 1.2199 0.01934 0.01354 -0.0049 0.0037 1.0000
11.500 1.2313 0.02006 0.01429 -0.0030 0.0033 1.0000
11.750 1.2417 0.02089 0.01520 -0.0011 0.0032 1.0000
12.000 1.2499 0.02190 0.01626 0.0008 0.0027 1.0000
12.250 1.2582 0.02298 0.01742 0.0027 0.0026 1.0000
12.500 1.2666 0.02411 0.01862 0.0043 0.0025 1.0000
12.750 1.2756 0.02524 0.01984 0.0057 0.0023 1.0000
13.000 1.2821 0.02663 0.02133 0.0071 0.0023 1.0000
13.250 1.2906 0.02791 0.02268 0.0082 0.0022 1.0000
13.500 1.2986 0.02928 0.02413 0.0092 0.0021 1.0000
13.750 1.3046 0.03087 0.02581 0.0102 0.0020 1.0000
14.000 1.3090 0.03266 0.02770 0.0112 0.0019 1.0000
14.250 1.3139 0.03446 0.02958 0.0119 0.0018 1.0000
14.500 1.3178 0.03640 0.03162 0.0126 0.0018 1.0000
14.750 1.3216 0.03840 0.03370 0.0131 0.0017 1.0000
15.000 1.3213 0.04086 0.03630 0.0135 0.0017 1.0000
15.250 1.3229 0.04320 0.03872 0.0138 0.0016 1.0000
15.500 1.3248 0.04555 0.04116 0.0139 0.0016 1.0000
15.750 1.3212 0.04862 0.04434 0.0139 0.0015 1.0000
16.000 1.3193 0.05162 0.04745 0.0137 0.0015 1.0000
16.250 1.3123 0.05535 0.05130 0.0132 0.0014 1.0000
16.500 1.3051 0.05929 0.05537 0.0124 0.0014 1.0000
16.750 1.2876 0.06482 0.06107 0.0110 0.0013 1.0000
17.000 1.2818 0.06891 0.06527 0.0097 0.0013 1.0000
17.250 1.2707 0.07398 0.07047 0.0079 0.0013 1.0000
17.500 1.2555 0.07990 0.07653 0.0057 0.0012 1.0000
17.750 1.2441 0.08541 0.08217 0.0033 0.0012 1.0000
18.000 1.2214 0.09318 0.09010 -0.0002 0.0012 1.0000
18.250 1.2007 0.10090 0.09796 -0.0039 0.0012 1.0000
18.500 1.1780 0.10940 0.10661 -0.0081 0.0012 1.0000
18.750 1.1863 0.11180 0.10905 -0.0092 0.0013 1.0000
19.000 1.1452 0.12455 0.12200 -0.0159 0.0012 1.0000
19.250 1.1255 0.13320 0.13078 -0.0205 0.0013 1.0000
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Polar data table (+)
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