GOE 142 (MVA H.19) AIRFOIL (goe142-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 142 (MVA H.19) AIRFOIL (goe142-il) Reynolds number: 100,000 Max Cl/Cd: 56.63 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe142-il-100000-n5.txt Download as CSV file: xf-goe142-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 142 (MVA H.19) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3873 0.10151 0.09659 -0.0105 1.0000 0.0382
-7.750 -0.3824 0.09867 0.09380 -0.0123 1.0000 0.0392
-7.500 -0.3790 0.09620 0.09139 -0.0147 1.0000 0.0403
-7.250 -0.3734 0.09378 0.08904 -0.0193 1.0000 0.0410
-7.000 -0.3631 0.09088 0.08617 -0.0248 1.0000 0.0413
-6.750 -0.3507 0.08763 0.08294 -0.0295 1.0000 0.0415
-6.500 -0.2960 0.07272 0.06847 -0.0317 1.0000 0.0418
-6.250 -0.2953 0.06706 0.06289 -0.0260 1.0000 0.0432
-5.750 -0.3152 0.07235 0.06777 -0.0333 1.0000 0.0434
-5.500 -0.3086 0.06970 0.06517 -0.0315 1.0000 0.0457
-5.250 -0.2970 0.06681 0.06228 -0.0328 1.0000 0.0481
-5.000 -0.2826 0.06368 0.05912 -0.0349 1.0000 0.0501
-4.750 -0.2509 0.06074 0.05593 -0.0421 1.0000 0.0540
-4.500 -0.2303 0.05754 0.05256 -0.0443 1.0000 0.0543
-4.250 -0.2262 0.05204 0.04717 -0.0422 1.0000 0.0390
-4.000 -0.2059 0.04805 0.04305 -0.0440 0.9998 0.0351
-3.500 -0.1126 0.03698 0.03116 -0.0567 0.9892 0.0323
-3.250 -0.0732 0.03449 0.02844 -0.0606 0.9838 0.0354
-3.000 -0.0315 0.03038 0.02385 -0.0642 0.9772 0.0351
-2.750 0.0117 0.02676 0.01968 -0.0676 0.9720 0.0357
-2.500 0.0519 0.02395 0.01631 -0.0700 0.9653 0.0383
-2.250 0.0937 0.02155 0.01321 -0.0723 0.9591 0.0421
-2.000 0.1315 0.01986 0.01127 -0.0744 0.9516 0.0450
-1.750 0.1696 0.01882 0.00999 -0.0762 0.9434 0.0517
-1.500 0.2041 0.01758 0.00853 -0.0771 0.9329 0.0565
-1.250 0.2382 0.01681 0.00771 -0.0782 0.9218 0.0640
-1.000 0.2714 0.01607 0.00690 -0.0789 0.9097 0.0729
-0.750 0.3032 0.01547 0.00622 -0.0792 0.8963 0.0828
-0.500 0.3336 0.01498 0.00573 -0.0794 0.8813 0.0970
-0.250 0.3629 0.01452 0.00527 -0.0792 0.8652 0.1118
0.000 0.3919 0.01416 0.00492 -0.0790 0.8480 0.1388
0.250 0.4211 0.01373 0.00461 -0.0789 0.8301 0.1879
0.500 0.4475 0.01166 0.00438 -0.0780 0.8114 1.0000
0.750 0.4749 0.01171 0.00417 -0.0773 0.7899 1.0000
1.000 0.5018 0.01178 0.00403 -0.0766 0.7673 1.0000
1.250 0.5286 0.01187 0.00391 -0.0758 0.7440 1.0000
1.500 0.5550 0.01200 0.00386 -0.0751 0.7190 1.0000
1.750 0.5812 0.01214 0.00384 -0.0744 0.6935 1.0000
2.000 0.6073 0.01232 0.00384 -0.0737 0.6678 1.0000
2.250 0.6332 0.01252 0.00388 -0.0730 0.6419 1.0000
2.500 0.6590 0.01276 0.00395 -0.0723 0.6160 1.0000
2.750 0.6848 0.01301 0.00408 -0.0716 0.5899 1.0000
3.000 0.7104 0.01328 0.00422 -0.0710 0.5643 1.0000
3.250 0.7360 0.01357 0.00439 -0.0704 0.5393 1.0000
3.500 0.7614 0.01389 0.00459 -0.0698 0.5154 1.0000
3.750 0.7868 0.01422 0.00485 -0.0693 0.4914 1.0000
4.000 0.8121 0.01457 0.00512 -0.0687 0.4688 1.0000
4.250 0.8372 0.01494 0.00540 -0.0682 0.4471 1.0000
4.500 0.8625 0.01531 0.00573 -0.0677 0.4261 1.0000
4.750 0.8875 0.01571 0.00612 -0.0672 0.4064 1.0000
5.000 0.9124 0.01613 0.00650 -0.0667 0.3878 1.0000
5.250 0.9373 0.01655 0.00692 -0.0662 0.3696 1.0000
5.500 0.9621 0.01699 0.00737 -0.0657 0.3524 1.0000
5.750 0.9867 0.01746 0.00785 -0.0651 0.3362 1.0000
6.000 1.0111 0.01794 0.00840 -0.0646 0.3208 1.0000
6.250 1.0353 0.01845 0.00895 -0.0640 0.3060 1.0000
6.500 1.0594 0.01897 0.00953 -0.0635 0.2916 1.0000
6.750 1.0833 0.01952 0.01014 -0.0629 0.2775 1.0000
7.000 1.1068 0.02008 0.01082 -0.0623 0.2630 1.0000
7.250 1.1298 0.02064 0.01148 -0.0616 0.2465 1.0000
7.500 1.1521 0.02119 0.01211 -0.0609 0.2251 1.0000
7.750 1.1735 0.02179 0.01274 -0.0602 0.1994 1.0000
8.000 1.1947 0.02248 0.01346 -0.0594 0.1738 1.0000
8.250 1.2152 0.02328 0.01433 -0.0586 0.1465 1.0000
8.500 1.2335 0.02439 0.01534 -0.0576 0.1088 1.0000
8.750 1.2479 0.02607 0.01679 -0.0563 0.0708 1.0000
9.000 1.2600 0.02802 0.01859 -0.0546 0.0512 1.0000
9.250 1.2721 0.02982 0.02050 -0.0528 0.0425 1.0000
9.500 1.2833 0.03158 0.02244 -0.0509 0.0374 1.0000
9.750 1.2930 0.03335 0.02435 -0.0491 0.0330 1.0000
10.000 1.2981 0.03543 0.02660 -0.0468 0.0302 1.0000
10.250 1.3047 0.03730 0.02871 -0.0445 0.0284 1.0000
10.500 1.3077 0.03927 0.03088 -0.0419 0.0269 1.0000
10.750 1.3095 0.04136 0.03313 -0.0395 0.0256 1.0000
11.000 1.3101 0.04359 0.03550 -0.0375 0.0242 1.0000
11.250 1.3082 0.04618 0.03819 -0.0357 0.0230 1.0000
11.500 1.3050 0.04927 0.04138 -0.0341 0.0219 1.0000
11.750 1.3057 0.05199 0.04438 -0.0331 0.0211 1.0000
12.000 1.3045 0.05512 0.04776 -0.0322 0.0205 1.0000
12.250 1.3017 0.05859 0.05147 -0.0316 0.0200 1.0000
12.500 1.2971 0.06241 0.05554 -0.0315 0.0196 1.0000
12.750 1.2903 0.06665 0.06002 -0.0319 0.0193 1.0000
13.000 1.2814 0.07134 0.06496 -0.0329 0.0190 1.0000
13.250 1.2706 0.07652 0.07038 -0.0345 0.0189 1.0000
13.500 1.2578 0.08223 0.07633 -0.0368 0.0187 1.0000
13.750 1.2431 0.08856 0.08288 -0.0398 0.0187 1.0000
14.000 1.2268 0.09547 0.09001 -0.0434 0.0187 1.0000
14.250 1.2088 0.10309 0.09783 -0.0477 0.0188 1.0000
14.500 1.1897 0.11140 0.10633 -0.0527 0.0189 1.0000
14.750 1.1693 0.12061 0.11572 -0.0584 0.0191 1.0000
15.000 1.1477 0.13077 0.12603 -0.0647 0.0194 1.0000
15.250 1.1250 0.14205 0.13742 -0.0718 0.0198 1.0000
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Polar data table (+)
Polar graphs
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