GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 500,000 Max Cl/Cd: 103.04 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe308-il-500000.txt Download as CSV file: xf-goe308-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3241 0.09715 0.09503 -0.0280 1.0000 0.0204
-8.250 -0.3298 0.09499 0.09291 -0.0274 1.0000 0.0204
-8.000 -0.3413 0.09315 0.09113 -0.0258 1.0000 0.0205
-7.750 -0.3437 0.09042 0.08843 -0.0272 0.9985 0.0205
-7.500 -0.3171 0.08468 0.08266 -0.0360 0.9943 0.0206
-7.250 -0.3021 0.07816 0.07613 -0.0417 0.9897 0.0209
-7.000 -0.2810 0.07511 0.07308 -0.0432 0.9868 0.0215
-6.750 -0.2542 0.07129 0.06922 -0.0487 0.9838 0.0221
-6.500 -0.2318 0.06753 0.06544 -0.0535 0.9770 0.0230
-6.250 -0.1892 0.06205 0.05984 -0.0656 0.9718 0.0264
-6.000 -0.1620 0.05751 0.05521 -0.0707 0.9642 0.0266
-5.750 -0.1396 0.04946 0.04701 -0.0771 0.9587 0.0273
-5.500 -0.1172 0.04686 0.04436 -0.0787 0.9517 0.0280
-5.250 -0.0891 0.04466 0.04211 -0.0812 0.9459 0.0292
-5.000 -0.0589 0.04176 0.03911 -0.0842 0.9385 0.0315
-4.500 0.0005 0.03198 0.02881 -0.0898 0.9176 0.0368
-4.250 0.0281 0.03067 0.02741 -0.0909 0.9058 0.0384
-4.000 0.0557 0.02858 0.02513 -0.0916 0.8925 0.0418
-3.750 0.0787 0.02484 0.02103 -0.0913 0.8784 0.0479
-3.500 0.1035 0.02412 0.02021 -0.0912 0.8643 0.0500
-3.000 0.1403 0.01429 0.00894 -0.0863 0.8381 0.0408
-2.750 0.1649 0.01270 0.00694 -0.0852 0.8250 0.0397
-2.500 0.1903 0.01185 0.00585 -0.0844 0.8114 0.0396
-2.250 0.2156 0.01121 0.00503 -0.0836 0.7976 0.0398
-2.000 0.2408 0.01073 0.00442 -0.0828 0.7830 0.0404
-1.750 0.2657 0.01035 0.00392 -0.0819 0.7671 0.0415
-1.500 0.2902 0.00999 0.00344 -0.0810 0.7502 0.0420
-1.250 0.3144 0.00970 0.00305 -0.0800 0.7316 0.0428
-1.000 0.3380 0.00949 0.00274 -0.0788 0.7103 0.0435
-0.750 0.3614 0.00936 0.00248 -0.0777 0.6876 0.0442
-0.500 0.3844 0.00928 0.00227 -0.0765 0.6634 0.0449
-0.250 0.4076 0.00924 0.00211 -0.0753 0.6400 0.0458
0.000 0.4304 0.00921 0.00195 -0.0741 0.6173 0.0492
0.250 0.4536 0.00921 0.00187 -0.0730 0.5942 0.0539
0.500 0.4765 0.00923 0.00192 -0.0718 0.5716 0.0852
0.750 0.5007 0.00936 0.00198 -0.0710 0.5496 0.1045
1.000 0.5244 0.00948 0.00202 -0.0701 0.5297 0.1151
1.250 0.5485 0.00961 0.00205 -0.0693 0.5119 0.1221
1.500 0.5722 0.00967 0.00207 -0.0684 0.4960 0.1296
1.750 0.5962 0.00978 0.00211 -0.0676 0.4823 0.1376
2.000 0.6201 0.00985 0.00217 -0.0668 0.4701 0.1481
2.250 0.6447 0.00991 0.00224 -0.0661 0.4600 0.1609
2.500 0.6687 0.00997 0.00234 -0.0654 0.4512 0.1900
2.750 0.6863 0.00944 0.00248 -0.0635 0.4437 0.4922
3.000 0.7968 0.00898 0.00304 -0.0817 0.4287 0.9915
3.250 0.8625 0.00917 0.00316 -0.0903 0.4191 1.0000
3.500 0.8850 0.00930 0.00326 -0.0892 0.4132 1.0000
3.750 0.9071 0.00946 0.00338 -0.0880 0.4078 1.0000
4.000 0.9299 0.00955 0.00349 -0.0870 0.4021 1.0000
4.250 0.9517 0.00971 0.00363 -0.0858 0.3966 1.0000
4.500 0.9738 0.00985 0.00377 -0.0847 0.3912 1.0000
4.750 0.9958 0.00997 0.00391 -0.0835 0.3851 1.0000
5.000 1.0169 0.01011 0.00404 -0.0822 0.3762 1.0000
5.250 1.0377 0.01026 0.00417 -0.0808 0.3660 1.0000
5.500 1.0592 0.01036 0.00430 -0.0795 0.3567 1.0000
5.750 1.0798 0.01052 0.00445 -0.0781 0.3471 1.0000
6.000 1.0999 0.01069 0.00460 -0.0766 0.3345 1.0000
6.250 1.1200 0.01087 0.00478 -0.0751 0.3211 1.0000
6.500 1.1396 0.01108 0.00496 -0.0735 0.3030 1.0000
6.750 1.1569 0.01142 0.00518 -0.0716 0.2756 1.0000
7.000 1.1701 0.01202 0.00554 -0.0690 0.2298 1.0000
7.250 1.1775 0.01304 0.00617 -0.0654 0.1706 1.0000
7.500 1.1745 0.01475 0.00722 -0.0602 0.0749 1.0000
7.750 1.1763 0.01612 0.00835 -0.0556 0.0257 1.0000
8.000 1.1916 0.01662 0.00893 -0.0534 0.0231 1.0000
8.250 1.2044 0.01725 0.00963 -0.0507 0.0209 1.0000
8.500 1.2137 0.01807 0.01057 -0.0474 0.0193 1.0000
8.750 1.2230 0.01870 0.01127 -0.0441 0.0187 1.0000
9.000 1.2314 0.01934 0.01199 -0.0407 0.0180 1.0000
9.250 1.2395 0.02003 0.01278 -0.0375 0.0173 1.0000
9.500 1.2470 0.02082 0.01363 -0.0343 0.0164 1.0000
9.750 1.2531 0.02172 0.01460 -0.0311 0.0156 1.0000
10.000 1.2546 0.02293 0.01590 -0.0275 0.0150 1.0000
10.250 1.2541 0.02435 0.01741 -0.0239 0.0146 1.0000
10.500 1.2503 0.02610 0.01927 -0.0204 0.0143 1.0000
10.750 1.2398 0.02853 0.02182 -0.0167 0.0139 1.0000
11.000 1.2398 0.03041 0.02378 -0.0145 0.0139 1.0000
11.250 1.2478 0.03175 0.02523 -0.0131 0.0135 1.0000
11.500 1.2496 0.03370 0.02726 -0.0114 0.0134 1.0000
11.750 1.2523 0.03567 0.02932 -0.0099 0.0131 1.0000
12.000 1.2567 0.03755 0.03129 -0.0088 0.0126 1.0000
12.250 1.2599 0.03961 0.03343 -0.0078 0.0122 1.0000
12.500 1.2621 0.04185 0.03575 -0.0066 0.0121 1.0000
12.750 1.2661 0.04393 0.03790 -0.0059 0.0118 1.0000
13.000 1.2693 0.04615 0.04019 -0.0050 0.0116 1.0000
13.250 1.2724 0.04841 0.04252 -0.0042 0.0112 1.0000
13.500 1.2761 0.05065 0.04484 -0.0034 0.0110 1.0000
13.750 1.2798 0.05291 0.04715 -0.0026 0.0108 1.0000
14.000 1.2850 0.05508 0.04939 -0.0016 0.0106 1.0000
14.250 1.2971 0.05688 0.05120 0.0005 0.0103 1.0000
14.500 1.2981 0.05948 0.05395 0.0006 0.0104 1.0000
14.750 1.3061 0.06196 0.05653 0.0020 0.0103 1.0000
15.000 1.3087 0.06495 0.05966 0.0027 0.0103 1.0000
15.250 1.3076 0.06835 0.06322 0.0030 0.0103 1.0000
15.500 1.3004 0.07191 0.06697 0.0023 0.0105 1.0000
15.750 1.2957 0.07611 0.07133 0.0024 0.0104 1.0000
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Polar data table (+)
Polar graphs
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