E231 (e231-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: E231 (e231-il) Reynolds number: 1,000,000 Max Cl/Cd: 85.59 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e231-il-1000000-n5.txt Download as CSV file: xf-e231-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E231
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4650 0.04690 0.04440 -0.0774 0.8242 0.0029
-8.500 -0.4796 0.04003 0.03719 -0.0720 0.8165 0.0028
-8.250 -0.5016 0.03285 0.02959 -0.0669 0.8129 0.0026
-8.000 -0.5129 0.02682 0.02305 -0.0620 0.8093 0.0025
-7.750 -0.5109 0.02266 0.01839 -0.0582 0.8061 0.0025
-7.500 -0.4991 0.01994 0.01526 -0.0558 0.8034 0.0024
-7.250 -0.4819 0.01804 0.01303 -0.0541 0.8011 0.0024
-7.000 -0.4615 0.01660 0.01136 -0.0529 0.7987 0.0024
-6.750 -0.4398 0.01540 0.00997 -0.0519 0.7962 0.0024
-6.500 -0.4176 0.01431 0.00870 -0.0510 0.7937 0.0024
-6.250 -0.3941 0.01359 0.00785 -0.0503 0.7913 0.0024
-6.000 -0.3711 0.01278 0.00691 -0.0494 0.7889 0.0024
-5.750 -0.3473 0.01218 0.00620 -0.0488 0.7867 0.0024
-5.500 -0.3233 0.01158 0.00552 -0.0481 0.7844 0.0025
-5.250 -0.2985 0.01113 0.00501 -0.0477 0.7818 0.0025
-5.000 -0.2736 0.01069 0.00451 -0.0471 0.7791 0.0025
-4.750 -0.2483 0.01034 0.00410 -0.0467 0.7766 0.0026
-4.500 -0.2229 0.01001 0.00371 -0.0463 0.7742 0.0027
-4.250 -0.1970 0.00972 0.00336 -0.0460 0.7718 0.0028
-4.000 -0.1711 0.00941 0.00301 -0.0457 0.7691 0.0031
-3.750 -0.1447 0.00917 0.00275 -0.0455 0.7662 0.0035
-3.500 -0.1182 0.00897 0.00253 -0.0453 0.7634 0.0045
-3.250 -0.0916 0.00879 0.00232 -0.0451 0.7606 0.0060
-3.000 -0.0651 0.00860 0.00215 -0.0450 0.7579 0.0117
-2.750 -0.0384 0.00841 0.00200 -0.0449 0.7548 0.0219
-2.500 -0.0131 0.00809 0.00185 -0.0445 0.7513 0.0592
-2.250 0.0104 0.00763 0.00168 -0.0440 0.7477 0.1408
-2.000 0.0348 0.00728 0.00155 -0.0435 0.7440 0.2132
-1.750 0.0585 0.00686 0.00144 -0.0430 0.7395 0.3061
-1.500 0.0817 0.00645 0.00133 -0.0423 0.7345 0.4018
-1.250 0.1049 0.00608 0.00123 -0.0416 0.7299 0.4934
-1.000 0.1272 0.00567 0.00115 -0.0407 0.7246 0.5945
-0.750 0.1469 0.00519 0.00107 -0.0391 0.7190 0.7171
-0.500 0.1698 0.00497 0.00111 -0.0380 0.7132 0.7981
-0.250 0.1963 0.00496 0.00115 -0.0377 0.7064 0.8295
0.000 0.2233 0.00498 0.00117 -0.0375 0.6997 0.8471
0.250 0.2508 0.00502 0.00118 -0.0375 0.6918 0.8580
0.500 0.2782 0.00506 0.00121 -0.0374 0.6837 0.8670
0.750 0.3052 0.00512 0.00123 -0.0372 0.6741 0.8744
1.000 0.3324 0.00518 0.00126 -0.0371 0.6635 0.8808
1.250 0.3593 0.00525 0.00129 -0.0370 0.6523 0.8869
1.500 0.3857 0.00534 0.00135 -0.0367 0.6394 0.8926
1.750 0.4118 0.00545 0.00140 -0.0364 0.6240 0.8981
2.000 0.4373 0.00557 0.00146 -0.0361 0.6058 0.9022
2.250 0.4624 0.00572 0.00154 -0.0356 0.5842 0.9062
2.500 0.4869 0.00590 0.00163 -0.0350 0.5607 0.9101
2.750 0.5114 0.00609 0.00172 -0.0345 0.5349 0.9130
3.000 0.5351 0.00631 0.00182 -0.0339 0.5055 0.9150
3.250 0.5586 0.00654 0.00194 -0.0332 0.4766 0.9169
3.500 0.5816 0.00680 0.00209 -0.0325 0.4465 0.9189
3.750 0.6043 0.00706 0.00224 -0.0317 0.4171 0.9212
4.000 0.6267 0.00733 0.00239 -0.0309 0.3876 0.9234
4.250 0.6494 0.00759 0.00255 -0.0302 0.3616 0.9256
4.500 0.6714 0.00787 0.00272 -0.0293 0.3344 0.9280
4.750 0.6931 0.00814 0.00290 -0.0284 0.3082 0.9302
5.000 0.7150 0.00840 0.00308 -0.0275 0.2866 0.9323
5.250 0.7368 0.00865 0.00327 -0.0266 0.2669 0.9347
5.500 0.7574 0.00894 0.00347 -0.0254 0.2442 0.9375
5.750 0.7775 0.00924 0.00369 -0.0242 0.2222 0.9406
6.000 0.7978 0.00952 0.00390 -0.0231 0.2041 0.9434
6.250 0.8183 0.00977 0.00411 -0.0219 0.1897 0.9463
6.500 0.8368 0.01008 0.00437 -0.0204 0.1705 0.9499
6.750 0.8540 0.01035 0.00460 -0.0187 0.1560 0.9542
7.000 0.8708 0.01067 0.00486 -0.0169 0.1411 0.9590
7.250 0.8898 0.01099 0.00516 -0.0155 0.1281 0.9643
7.500 0.9099 0.01131 0.00546 -0.0145 0.1173 0.9699
7.750 0.9341 0.01172 0.00584 -0.0145 0.1038 0.9742
8.000 0.9585 0.01220 0.00625 -0.0146 0.0888 0.9790
8.250 0.9842 0.01263 0.00666 -0.0151 0.0784 0.9835
8.500 1.0105 0.01319 0.00714 -0.0158 0.0645 0.9873
8.750 1.0372 0.01366 0.00761 -0.0165 0.0559 0.9920
9.000 1.0608 0.01423 0.00813 -0.0167 0.0459 1.0000
9.250 1.0714 0.01474 0.00859 -0.0142 0.0381 1.0000
9.500 1.0851 0.01522 0.00907 -0.0122 0.0329 1.0000
9.750 1.0981 0.01579 0.00961 -0.0103 0.0264 1.0000
10.000 1.1110 0.01641 0.01021 -0.0085 0.0208 1.0000
10.250 1.1238 0.01708 0.01085 -0.0067 0.0159 1.0000
10.500 1.1374 0.01772 0.01149 -0.0050 0.0123 1.0000
10.750 1.1519 0.01833 0.01214 -0.0036 0.0111 1.0000
11.000 1.1654 0.01901 0.01284 -0.0021 0.0088 1.0000
11.250 1.1780 0.01977 0.01362 -0.0005 0.0068 1.0000
11.500 1.1892 0.02063 0.01450 0.0012 0.0046 1.0000
11.750 1.2027 0.02137 0.01528 0.0025 0.0042 1.0000
12.000 1.2124 0.02237 0.01631 0.0042 0.0024 1.0000
12.250 1.2249 0.02321 0.01720 0.0056 0.0022 1.0000
12.500 1.2358 0.02416 0.01819 0.0069 0.0017 1.0000
12.750 1.2464 0.02516 0.01927 0.0084 0.0014 1.0000
13.000 1.2549 0.02633 0.02050 0.0099 0.0010 1.0000
13.250 1.2677 0.02721 0.02144 0.0109 0.0012 1.0000
13.500 1.2742 0.02856 0.02286 0.0124 0.0009 1.0000
13.750 1.2821 0.02985 0.02423 0.0137 0.0008 1.0000
14.000 1.2891 0.03125 0.02571 0.0149 0.0007 1.0000
14.250 1.2939 0.03285 0.02741 0.0163 0.0007 1.0000
14.500 1.3017 0.03425 0.02887 0.0172 0.0007 1.0000
14.750 1.3062 0.03600 0.03072 0.0183 0.0006 1.0000
15.000 1.3115 0.03771 0.03252 0.0191 0.0006 1.0000
15.250 1.3165 0.03951 0.03440 0.0198 0.0006 1.0000
15.500 1.3211 0.04141 0.03640 0.0204 0.0006 1.0000
15.750 1.3166 0.04434 0.03947 0.0212 0.0006 1.0000
16.000 1.3211 0.04641 0.04162 0.0215 0.0006 1.0000
16.250 1.3236 0.04877 0.04406 0.0216 0.0005 1.0000
16.500 1.3201 0.05192 0.04734 0.0216 0.0005 1.0000
16.750 1.3163 0.05526 0.05080 0.0214 0.0005 1.0000
17.000 1.3130 0.05865 0.05430 0.0209 0.0005 1.0000
17.250 1.3095 0.06219 0.05795 0.0201 0.0005 1.0000
17.500 1.3053 0.06599 0.06185 0.0191 0.0005 1.0000
17.750 1.2908 0.07147 0.06749 0.0175 0.0005 1.0000
18.000 1.2863 0.07558 0.07170 0.0160 0.0005 1.0000
18.250 1.2735 0.08123 0.07749 0.0137 0.0005 1.0000
18.500 1.2563 0.08783 0.08424 0.0109 0.0005 1.0000
18.750 1.2452 0.09356 0.09008 0.0082 0.0005 1.0000
19.000 1.2303 0.10014 0.09679 0.0050 0.0005 1.0000
19.250 1.2154 0.10690 0.10367 0.0016 0.0005 1.0000
|
Polar data table (+)
Polar graphs
<< Back to E231 (e231-il)