BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-14 AIRFOIL (vr14-il) Reynolds number: 50,000 Max Cl/Cd: 29.01 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr14-il-50000-n5.txt Download as CSV file: xf-vr14-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5336 0.09921 0.09271 -0.0012 1.0000 0.1127
-8.000 -0.5370 0.09557 0.08914 -0.0049 1.0000 0.1176
-7.500 -0.4564 0.07222 0.06602 -0.0224 1.0000 0.0626
-7.000 -0.5206 0.07183 0.06481 -0.0228 1.0000 0.0503
-6.750 -0.5113 0.06761 0.06055 -0.0230 1.0000 0.0497
-6.500 -0.5019 0.06352 0.05637 -0.0232 1.0000 0.0491
-6.250 -0.4917 0.05953 0.05224 -0.0232 1.0000 0.0482
-6.000 -0.4804 0.05561 0.04811 -0.0230 1.0000 0.0471
-5.750 -0.4682 0.05182 0.04405 -0.0225 1.0000 0.0462
-5.500 -0.4550 0.04820 0.04013 -0.0216 1.0000 0.0456
-5.250 -0.4408 0.04489 0.03645 -0.0204 1.0000 0.0460
-5.000 -0.4257 0.04192 0.03303 -0.0189 1.0000 0.0477
-4.750 -0.4096 0.03923 0.02980 -0.0170 1.0000 0.0495
-4.500 -0.3923 0.03670 0.02677 -0.0150 1.0000 0.0502
-4.250 -0.3741 0.03411 0.02378 -0.0132 1.0000 0.0510
-4.000 -0.3562 0.03183 0.02142 -0.0120 1.0000 0.0542
-3.750 -0.3362 0.03014 0.01942 -0.0105 1.0000 0.0588
-3.500 -0.3137 0.02832 0.01721 -0.0090 1.0000 0.0612
-3.250 -0.2903 0.02676 0.01530 -0.0077 1.0000 0.0649
-3.000 -0.2677 0.02540 0.01392 -0.0067 1.0000 0.0711
-2.750 -0.2423 0.02421 0.01252 -0.0057 1.0000 0.0752
-2.500 -0.2169 0.02318 0.01141 -0.0051 1.0000 0.0825
-2.250 -0.1930 0.02242 0.01043 -0.0043 1.0000 0.0904
-2.000 -0.1712 0.02164 0.00959 -0.0032 1.0000 0.0973
-1.750 -0.1494 0.02101 0.00889 -0.0021 1.0000 0.1093
-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 0.0491 0.01794 0.00765 -0.0048 0.9972 1.0000
0.250 0.0947 0.01825 0.00779 -0.0089 0.9855 1.0000
0.500 0.1548 0.01850 0.00789 -0.0156 0.9669 1.0000
0.750 0.2278 0.01851 0.00784 -0.0242 0.9431 1.0000
1.000 0.2743 0.01850 0.00779 -0.0275 0.9193 1.0000
1.250 0.3146 0.01848 0.00777 -0.0294 0.8993 1.0000
1.500 0.3464 0.01846 0.00777 -0.0296 0.8763 1.0000
1.750 0.3760 0.01841 0.00774 -0.0291 0.8518 1.0000
2.000 0.4029 0.01833 0.00768 -0.0279 0.8248 1.0000
2.250 0.4275 0.01825 0.00760 -0.0262 0.7941 1.0000
2.500 0.4513 0.01816 0.00751 -0.0243 0.7593 1.0000
2.750 0.4734 0.01811 0.00746 -0.0221 0.7160 1.0000
3.000 0.4947 0.01811 0.00737 -0.0197 0.6592 1.0000
3.250 0.5157 0.01821 0.00721 -0.0170 0.5824 1.0000
3.500 0.5351 0.01865 0.00713 -0.0144 0.4985 1.0000
3.750 0.5543 0.01937 0.00743 -0.0125 0.4352 1.0000
4.000 0.5745 0.02014 0.00789 -0.0111 0.3905 1.0000
4.250 0.5962 0.02091 0.00843 -0.0101 0.3589 1.0000
4.500 0.6187 0.02166 0.00904 -0.0092 0.3345 1.0000
4.750 0.6418 0.02241 0.00974 -0.0085 0.3146 1.0000
5.000 0.6655 0.02316 0.01043 -0.0078 0.2982 1.0000
5.250 0.6896 0.02391 0.01116 -0.0072 0.2832 1.0000
5.500 0.7139 0.02466 0.01195 -0.0066 0.2696 1.0000
5.750 0.7387 0.02546 0.01289 -0.0060 0.2580 1.0000
6.000 0.7631 0.02631 0.01383 -0.0055 0.2467 1.0000
6.250 0.7872 0.02718 0.01478 -0.0049 0.2359 1.0000
6.500 0.8112 0.02810 0.01576 -0.0043 0.2262 1.0000
6.750 0.8345 0.02907 0.01699 -0.0037 0.2153 1.0000
7.000 0.8568 0.03001 0.01809 -0.0030 0.2038 1.0000
7.250 0.8785 0.03094 0.01917 -0.0022 0.1926 1.0000
7.500 0.8999 0.03184 0.02013 -0.0014 0.1817 1.0000
7.750 0.9204 0.03284 0.02136 -0.0006 0.1703 1.0000
8.000 0.9407 0.03420 0.02309 0.0003 0.1601 1.0000
8.250 0.9605 0.03556 0.02465 0.0012 0.1507 1.0000
8.500 0.9796 0.03655 0.02569 0.0021 0.1405 1.0000
8.750 0.9959 0.03792 0.02739 0.0033 0.1292 1.0000
9.000 1.0110 0.03953 0.02932 0.0045 0.1188 1.0000
9.250 1.0259 0.04109 0.03108 0.0056 0.1103 1.0000
9.500 1.0400 0.04286 0.03313 0.0068 0.1029 1.0000
9.750 1.0494 0.04523 0.03585 0.0082 0.0957 1.0000
10.000 1.0616 0.04654 0.03725 0.0095 0.0891 1.0000
10.250 1.0651 0.04977 0.04089 0.0110 0.0847 1.0000
10.500 1.0629 0.05349 0.04504 0.0125 0.0812 1.0000
10.750 1.0648 0.05606 0.04781 0.0139 0.0779 1.0000
11.000 1.0692 0.05807 0.04985 0.0152 0.0748 1.0000
11.250 1.0467 0.06279 0.05493 0.0167 0.0738 1.0000
11.500 1.0205 0.06818 0.06057 0.0165 0.0735 1.0000
11.750 0.9909 0.07498 0.06755 0.0140 0.0738 1.0000
12.000 0.9590 0.08359 0.07625 0.0091 0.0745 1.0000
12.250 0.9262 0.09433 0.08702 0.0021 0.0752 1.0000
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Polar data table (+)
Polar graphs
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