D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 50,000 Max Cl/Cd: 20.55 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1182-il-50000-n5.txt Download as CSV file: xf-dga1182-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1182
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6210 0.11190 0.10592 0.0118 1.0000 0.1176
-8.750 -0.6289 0.10867 0.10278 0.0075 1.0000 0.1239
-8.500 -0.6480 0.10519 0.09946 -0.0007 1.0000 0.1256
-8.250 -0.6194 0.10018 0.09440 0.0064 1.0000 0.1323
-8.000 -0.6353 0.09657 0.09089 -0.0013 1.0000 0.1394
-7.500 -0.5302 0.07082 0.06538 -0.0158 1.0000 0.0755
-7.000 -0.6038 0.07146 0.06497 -0.0194 1.0000 0.0530
-6.750 -0.5924 0.06652 0.06012 -0.0192 1.0000 0.0509
-6.500 -0.5817 0.06214 0.05558 -0.0199 1.0000 0.0491
-6.250 -0.5691 0.05781 0.05102 -0.0207 1.0000 0.0471
-6.000 -0.5541 0.05346 0.04632 -0.0211 1.0000 0.0446
-5.750 -0.5320 0.05033 0.04228 -0.0208 1.0000 0.0406
-5.500 -0.5149 0.04608 0.03783 -0.0206 1.0000 0.0395
-5.250 -0.4953 0.04254 0.03398 -0.0202 1.0000 0.0385
-5.000 -0.4739 0.03929 0.03036 -0.0196 1.0000 0.0377
-4.750 -0.4509 0.03631 0.02696 -0.0189 1.0000 0.0371
-4.500 -0.4264 0.03357 0.02383 -0.0180 1.0000 0.0368
-4.250 -0.4009 0.03118 0.02106 -0.0171 1.0000 0.0375
-4.000 -0.3747 0.02928 0.01877 -0.0161 1.0000 0.0398
-3.750 -0.3495 0.02713 0.01644 -0.0150 1.0000 0.0417
-3.500 -0.3250 0.02531 0.01455 -0.0138 1.0000 0.0432
-3.250 -0.3014 0.02388 0.01301 -0.0125 1.0000 0.0453
-3.000 -0.2779 0.02274 0.01169 -0.0114 1.0000 0.0499
-2.750 -0.2491 0.02155 0.01036 -0.0117 0.9846 0.0583
-2.500 -0.2176 0.02055 0.00913 -0.0123 0.9627 0.0683
-2.250 -0.1866 0.01910 0.00820 -0.0132 0.9428 0.1565
-2.000 -0.1626 0.01793 0.00751 -0.0126 0.9237 0.4658
-1.750 -0.1408 0.01697 0.00710 -0.0111 0.8977 0.5551
-1.500 -0.1087 0.01684 0.00661 -0.0118 0.8630 0.5604
-1.250 -0.0763 0.01675 0.00621 -0.0125 0.8245 0.5670
-1.000 -0.0458 0.01669 0.00587 -0.0128 0.7852 0.5722
-0.750 -0.0170 0.01664 0.00557 -0.0127 0.7459 0.5765
-0.500 0.0107 0.01660 0.00534 -0.0125 0.7063 0.5827
-0.250 0.0373 0.01657 0.00514 -0.0120 0.6678 0.5921
0.000 0.0631 0.01654 0.00499 -0.0114 0.6343 0.6044
0.250 0.0883 0.01647 0.00487 -0.0107 0.6071 0.6222
0.500 0.1123 0.01636 0.00484 -0.0096 0.5766 0.6533
0.750 0.1393 0.01605 0.00497 -0.0083 0.5405 0.8205
1.000 0.1694 0.01617 0.00498 -0.0086 0.5073 0.8975
1.250 0.2069 0.01625 0.00500 -0.0106 0.4746 0.9551
1.500 0.2378 0.01645 0.00506 -0.0115 0.4430 1.0000
1.750 0.2616 0.01686 0.00518 -0.0109 0.3989 1.0000
2.000 0.2849 0.01744 0.00533 -0.0103 0.3619 1.0000
2.250 0.3092 0.01791 0.00558 -0.0099 0.3350 1.0000
2.500 0.3345 0.01823 0.00587 -0.0096 0.3155 1.0000
2.750 0.3605 0.01844 0.00622 -0.0093 0.2953 1.0000
3.000 0.3854 0.01888 0.00651 -0.0089 0.2074 1.0000
3.250 0.4082 0.01986 0.00706 -0.0085 0.1948 1.0000
3.500 0.4305 0.02120 0.00826 -0.0080 0.1838 1.0000
3.750 0.4540 0.02287 0.00992 -0.0076 0.1713 1.0000
4.000 0.4803 0.02465 0.01166 -0.0072 0.1583 1.0000
4.250 0.5067 0.02656 0.01358 -0.0070 0.1391 1.0000
4.500 0.5322 0.02763 0.01490 -0.0066 0.1251 1.0000
4.750 0.5585 0.02862 0.01623 -0.0062 0.1164 1.0000
5.000 0.5848 0.02978 0.01764 -0.0057 0.1097 1.0000
5.250 0.6110 0.03106 0.01920 -0.0053 0.1043 1.0000
5.500 0.6369 0.03260 0.02098 -0.0049 0.1008 1.0000
5.750 0.6626 0.03433 0.02312 -0.0043 0.0978 1.0000
6.000 0.6874 0.03625 0.02549 -0.0038 0.0952 1.0000
6.250 0.7103 0.03774 0.02728 -0.0033 0.0887 1.0000
6.500 0.7326 0.03941 0.02933 -0.0028 0.0824 1.0000
6.750 0.7541 0.04191 0.03213 -0.0023 0.0791 1.0000
7.000 0.7724 0.04565 0.03664 -0.0012 0.0761 1.0000
7.250 0.7892 0.04838 0.03982 -0.0005 0.0695 1.0000
7.500 0.8019 0.05182 0.04376 0.0002 0.0632 1.0000
7.750 0.8120 0.05555 0.04799 0.0009 0.0576 1.0000
8.000 0.8232 0.05839 0.05111 0.0014 0.0524 1.0000
8.250 0.8237 0.06387 0.05709 0.0016 0.0510 1.0000
8.500 0.8208 0.06910 0.06268 0.0013 0.0498 1.0000
8.750 0.8148 0.07421 0.06803 0.0004 0.0489 1.0000
9.000 0.8058 0.07934 0.07332 -0.0011 0.0484 1.0000
9.250 0.7936 0.08448 0.07854 -0.0031 0.0485 1.0000
9.500 0.7811 0.09016 0.08413 -0.0066 0.0490 1.0000
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Polar data table (+)
Polar graphs
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