BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V43015-2.48 AIRFOIL (v43015-il) Reynolds number: 50,000 Max Cl/Cd: 23.53 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v43015-il-50000.txt Download as CSV file: xf-v43015-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V43015-2.48 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2806 0.10957 0.10248 -0.0059 1.0000 0.4212
-9.500 -0.2808 0.10797 0.10096 -0.0041 1.0000 0.4441
-9.250 -0.2901 0.10725 0.10034 -0.0019 1.0000 0.4650
-9.000 -0.2652 0.10287 0.09601 -0.0011 1.0000 0.4863
-8.750 -0.2483 0.09960 0.09278 -0.0002 1.0000 0.5069
-8.250 -0.2387 0.09507 0.08841 0.0029 1.0000 0.5429
-8.000 -0.2423 0.09373 0.08717 0.0052 1.0000 0.5603
-7.750 -0.2165 0.08884 0.08231 0.0041 1.0000 0.5652
-7.500 -0.2108 0.08623 0.07977 0.0049 1.0000 0.5719
-7.250 -0.2226 0.08469 0.07836 0.0074 1.0000 0.5810
-7.000 -0.2184 0.08114 0.07489 0.0070 1.0000 0.5684
-6.750 -0.3383 0.07586 0.06998 0.0040 1.0000 0.4345
-6.500 -0.4509 0.07143 0.06588 0.0068 1.0000 0.3870
-6.250 -0.5240 0.06523 0.05971 0.0072 1.0000 0.3474
-6.000 -0.5755 0.05876 0.05296 0.0070 1.0000 0.3077
-5.750 -0.6025 0.05289 0.04627 0.0072 1.0000 0.2619
-5.500 -0.6034 0.04918 0.04173 0.0090 1.0000 0.2288
-5.250 -0.5923 0.04638 0.03850 0.0108 1.0000 0.2097
-5.000 -0.5818 0.04455 0.03604 0.0133 1.0000 0.1943
-4.750 -0.5677 0.04237 0.03369 0.0151 1.0000 0.1874
-4.500 -0.5548 0.04175 0.03237 0.0178 1.0000 0.1781
-4.250 -0.5384 0.03989 0.03044 0.0192 1.0000 0.1743
-4.000 -0.5221 0.03860 0.02891 0.0208 1.0000 0.1686
-3.750 -0.5073 0.03867 0.02838 0.0232 1.0000 0.1621
-3.500 -0.4902 0.03741 0.02707 0.0243 1.0000 0.1598
-3.250 -0.4617 0.03644 0.02599 0.0235 0.9958 0.1571
-3.000 -0.3950 0.03573 0.02504 0.0165 0.9757 0.1571
-2.750 -0.3255 0.03507 0.02426 0.0094 0.9556 0.1578
-2.500 -0.2568 0.03443 0.02360 0.0028 0.9347 0.1586
-2.250 -0.1909 0.03365 0.02288 -0.0032 0.9129 0.1644
-2.000 -0.1312 0.03273 0.02203 -0.0083 0.8907 0.1738
-1.750 0.3386 0.02880 0.02097 -0.0664 0.8835 1.0000
-1.500 0.3976 0.02729 0.01919 -0.0713 0.8490 1.0000
-1.250 0.4382 0.02624 0.01789 -0.0727 0.8123 1.0000
-1.000 0.4659 0.02564 0.01703 -0.0720 0.7757 1.0000
-0.750 0.4875 0.02535 0.01649 -0.0704 0.7411 1.0000
-0.500 0.5078 0.02519 0.01607 -0.0686 0.7098 1.0000
-0.250 0.5254 0.02522 0.01587 -0.0666 0.6802 1.0000
0.000 0.5438 0.02532 0.01571 -0.0647 0.6544 1.0000
0.250 0.5587 0.02560 0.01583 -0.0625 0.6291 1.0000
0.500 0.5750 0.02587 0.01592 -0.0605 0.6066 1.0000
0.750 0.5914 0.02621 0.01608 -0.0586 0.5864 1.0000
1.000 0.6075 0.02662 0.01635 -0.0566 0.5678 1.0000
1.250 0.6235 0.02709 0.01669 -0.0547 0.5507 1.0000
1.500 0.6399 0.02758 0.01705 -0.0528 0.5354 1.0000
1.750 0.6591 0.02801 0.01728 -0.0512 0.5220 1.0000
2.000 0.6718 0.02877 0.01806 -0.0491 0.5082 1.0000
2.250 0.6858 0.02957 0.01881 -0.0470 0.4961 1.0000
2.500 0.7055 0.03011 0.01917 -0.0455 0.4856 1.0000
2.750 0.7141 0.03121 0.02039 -0.0429 0.4746 1.0000
3.000 0.7356 0.03180 0.02077 -0.0416 0.4659 1.0000
3.250 0.7395 0.03323 0.02239 -0.0386 0.4565 1.0000
3.500 0.7605 0.03386 0.02286 -0.0372 0.4482 1.0000
3.750 0.7620 0.03551 0.02469 -0.0339 0.4400 1.0000
4.000 0.7768 0.03651 0.02565 -0.0319 0.4324 1.0000
4.250 0.7875 0.03785 0.02700 -0.0296 0.4257 1.0000
4.500 0.7839 0.03987 0.02921 -0.0259 0.4187 1.0000
4.750 0.8064 0.04057 0.02978 -0.0247 0.4118 1.0000
5.000 0.8016 0.04287 0.03222 -0.0211 0.4062 1.0000
5.250 0.7834 0.04589 0.03543 -0.0164 0.4008 1.0000
5.500 0.7931 0.04738 0.03691 -0.0141 0.3948 1.0000
5.750 0.8068 0.04891 0.03839 -0.0124 0.3896 1.0000
6.000 0.7410 0.05513 0.04482 -0.0052 0.3874 1.0000
6.250 0.6462 0.06388 0.05362 0.0015 0.3882 1.0000
6.500 0.5605 0.07494 0.06465 0.0011 0.3931 1.0000
6.750 0.5588 0.07878 0.06846 0.0013 0.3919 1.0000
7.750 0.3936 0.10628 0.09604 -0.0082 0.5115 1.0000
8.000 0.4346 0.11107 0.10083 -0.0097 0.5041 1.0000
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Polar data table (+)
Polar graphs
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