BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 50,000 Max Cl/Cd: 29.45 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr14-il-50000.txt Download as CSV file: xf-vr14-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-14 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5335 0.10725 0.10076 0.0111 1.0000 0.2133
-8.250 -0.5516 0.10554 0.09917 0.0070 1.0000 0.2211
-8.000 -0.5482 0.10194 0.09564 0.0070 1.0000 0.2355
-7.750 -0.5249 0.09698 0.09067 0.0105 1.0000 0.2564
-7.500 -0.5221 0.09370 0.08747 0.0107 1.0000 0.2742
-7.250 -0.5279 0.09091 0.08478 0.0100 1.0000 0.2921
-7.000 -0.5141 0.08696 0.08087 0.0123 1.0000 0.3158
-6.750 -0.5134 0.08386 0.07785 0.0135 1.0000 0.3412
-6.500 -0.5023 0.08065 0.07469 0.0166 1.0000 0.3755
-6.250 -0.4918 0.07769 0.07179 0.0206 1.0000 0.4203
-6.000 -0.4670 0.07457 0.06864 0.0274 1.0000 0.4932
-5.750 -0.4302 0.07076 0.06479 0.0335 1.0000 0.5783
-5.500 -0.3883 0.06694 0.06092 0.0391 1.0000 0.6865
-4.750 -0.3349 0.04324 0.03797 0.0226 1.0000 0.5889
-4.500 -0.4448 0.05483 0.04937 0.0327 1.0000 0.5861
-4.250 -0.4002 0.04020 0.03189 -0.0151 1.0000 0.1598
-4.000 -0.3787 0.03684 0.02793 -0.0136 1.0000 0.1424
-3.750 -0.3567 0.03455 0.02479 -0.0116 1.0000 0.1346
-3.500 -0.3356 0.03231 0.02208 -0.0099 1.0000 0.1349
-3.250 -0.3124 0.02989 0.01937 -0.0085 1.0000 0.1340
-3.000 -0.2885 0.02780 0.01701 -0.0072 1.0000 0.1367
-2.750 -0.2643 0.02613 0.01522 -0.0062 1.0000 0.1445
-2.500 -0.2369 0.02472 0.01347 -0.0051 1.0000 0.1488
-2.250 -0.2080 0.02332 0.01203 -0.0047 1.0000 0.1623
-2.000 -0.1779 0.02211 0.01077 -0.0045 1.0000 0.1769
-1.750 -0.0569 0.01682 0.00834 -0.0182 1.0000 1.0000
-1.500 -0.0437 0.01690 0.00797 -0.0156 1.0000 1.0000
-1.250 -0.0308 0.01701 0.00777 -0.0131 1.0000 1.0000
-1.000 -0.0175 0.01714 0.00764 -0.0108 1.0000 1.0000
-0.750 -0.0036 0.01730 0.00757 -0.0087 1.0000 1.0000
-0.500 0.0110 0.01748 0.00755 -0.0068 1.0000 1.0000
-0.250 0.0263 0.01769 0.00757 -0.0050 1.0000 1.0000
0.000 0.0423 0.01793 0.00765 -0.0034 1.0000 1.0000
0.250 0.0588 0.01820 0.00779 -0.0020 1.0000 1.0000
0.500 0.0757 0.01850 0.00798 -0.0008 1.0000 1.0000
0.750 0.0930 0.01884 0.00821 0.0003 1.0000 1.0000
1.000 0.1106 0.01921 0.00851 0.0013 1.0000 1.0000
1.250 0.1282 0.01963 0.00888 0.0021 1.0000 1.0000
1.500 0.1458 0.02011 0.00933 0.0029 1.0000 1.0000
1.750 0.1633 0.02064 0.00985 0.0035 1.0000 1.0000
2.000 0.1804 0.02126 0.01047 0.0039 1.0000 1.0000
2.250 0.2516 0.02231 0.01165 -0.0060 0.9762 1.0000
2.500 0.3511 0.02296 0.01256 -0.0197 0.9338 1.0000
2.750 0.4529 0.02242 0.01244 -0.0314 0.8835 1.0000
3.000 0.5113 0.02125 0.01154 -0.0328 0.8262 1.0000
3.250 0.5421 0.02007 0.01042 -0.0284 0.7572 1.0000
3.500 0.5605 0.01948 0.00957 -0.0226 0.6654 1.0000
3.750 0.5789 0.01966 0.00923 -0.0182 0.5795 1.0000
4.000 0.6000 0.02044 0.00952 -0.0158 0.5185 1.0000
4.250 0.6232 0.02140 0.01016 -0.0144 0.4753 1.0000
4.500 0.6475 0.02245 0.01099 -0.0133 0.4434 1.0000
4.750 0.6718 0.02354 0.01203 -0.0125 0.4169 1.0000
5.000 0.6963 0.02467 0.01309 -0.0117 0.3952 1.0000
5.250 0.7210 0.02591 0.01440 -0.0111 0.3774 1.0000
5.500 0.7452 0.02721 0.01576 -0.0105 0.3611 1.0000
5.750 0.7689 0.02856 0.01724 -0.0098 0.3455 1.0000
6.000 0.7924 0.03013 0.01898 -0.0092 0.3324 1.0000
6.250 0.8149 0.03175 0.02077 -0.0085 0.3186 1.0000
6.500 0.8364 0.03340 0.02259 -0.0077 0.3041 1.0000
6.750 0.8570 0.03515 0.02454 -0.0068 0.2897 1.0000
7.000 0.8767 0.03703 0.02668 -0.0059 0.2753 1.0000
7.250 0.8953 0.03899 0.02884 -0.0048 0.2605 1.0000
7.500 0.9123 0.04145 0.03159 -0.0038 0.2479 1.0000
7.750 0.9292 0.04421 0.03458 -0.0028 0.2372 1.0000
8.000 0.9452 0.04670 0.03725 -0.0016 0.2242 1.0000
8.250 0.9615 0.04907 0.03979 -0.0004 0.2110 1.0000
8.500 0.9556 0.05422 0.04570 0.0007 0.2046 1.0000
8.750 0.9648 0.05715 0.04879 0.0020 0.1935 1.0000
9.000 0.9832 0.05938 0.05101 0.0033 0.1824 1.0000
9.250 0.9668 0.06573 0.05785 0.0037 0.1814 1.0000
9.500 0.9487 0.07222 0.06460 0.0035 0.1814 1.0000
9.750 0.9303 0.07877 0.07129 0.0026 0.1821 1.0000
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Polar data table (+)
Polar graphs
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