BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-13 AIRFOIL (vr13-il) Reynolds number: 100,000 Max Cl/Cd: 40.15 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr13-il-100000.txt Download as CSV file: xf-vr13-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-13 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3814 0.11296 0.10837 -0.0084 1.0000 0.0778
-10.000 -0.3850 0.10956 0.10500 -0.0102 1.0000 0.0807
-9.750 -0.5115 0.11453 0.10975 -0.0007 1.0000 0.0716
-9.500 -0.5015 0.11097 0.10620 -0.0002 1.0000 0.0743
-9.250 -0.4975 0.10736 0.10260 -0.0017 1.0000 0.0771
-9.000 -0.4979 0.10358 0.09887 -0.0048 1.0000 0.0802
-8.750 -0.5086 0.09963 0.09502 -0.0123 1.0000 0.0824
-8.500 -0.5243 0.09546 0.09087 -0.0204 1.0000 0.0830
-8.250 -0.5383 0.09210 0.08737 -0.0256 1.0000 0.0834
-8.000 -0.4979 0.08685 0.08235 -0.0155 1.0000 0.0885
-7.750 -0.4978 0.08310 0.07863 -0.0176 1.0000 0.0919
-7.500 -0.5047 0.07880 0.07424 -0.0237 1.0000 0.0963
-7.250 -0.5150 0.07436 0.06960 -0.0277 1.0000 0.0988
-7.000 -0.4955 0.07056 0.06602 -0.0246 1.0000 0.1029
-6.750 -0.4936 0.06753 0.06286 -0.0259 1.0000 0.1109
-6.500 -0.4925 0.06358 0.05888 -0.0253 1.0000 0.1159
-6.250 -0.4931 0.06211 0.05723 -0.0237 1.0000 0.1267
-6.000 -0.4888 0.05838 0.05365 -0.0212 1.0000 0.1323
-5.750 -0.4880 0.04778 0.04318 -0.0154 1.0000 0.1429
-5.500 -0.4866 0.05384 0.04902 -0.0160 1.0000 0.1518
-5.250 -0.4857 0.05138 0.04650 -0.0134 1.0000 0.1634
-5.000 -0.4827 0.04913 0.04416 -0.0108 1.0000 0.1779
-4.750 -0.4773 0.04698 0.04198 -0.0082 1.0000 0.1948
-4.500 -0.4732 0.04504 0.04003 -0.0054 1.0000 0.2225
-4.250 -0.4671 0.04315 0.03821 -0.0023 1.0000 0.2534
-4.000 -0.4596 0.04121 0.03633 0.0008 1.0000 0.2854
-3.750 -0.4012 0.03139 0.02378 -0.0012 1.0000 0.0941
-3.500 -0.3800 0.02900 0.02100 0.0004 1.0000 0.0914
-3.250 -0.3558 0.02676 0.01819 0.0019 1.0000 0.0868
-3.000 -0.3313 0.02521 0.01623 0.0031 1.0000 0.0860
-2.750 -0.3073 0.02400 0.01493 0.0037 1.0000 0.0897
-2.500 -0.2820 0.02285 0.01358 0.0044 1.0000 0.0907
-2.250 -0.2571 0.02191 0.01251 0.0051 1.0000 0.0927
-2.000 -0.2334 0.02138 0.01182 0.0059 1.0000 0.0974
-1.750 -0.2091 0.02038 0.01090 0.0064 1.0000 0.1014
-1.500 -0.1861 0.01978 0.01038 0.0071 1.0000 0.1065
-1.250 -0.1481 0.01922 0.00989 0.0048 0.9955 0.1188
-1.000 -0.0581 0.01573 0.00966 -0.0056 0.9999 1.0000
-0.750 0.0146 0.01607 0.00948 -0.0145 0.9867 1.0000
-0.500 0.0929 0.01620 0.00933 -0.0245 0.9709 1.0000
-0.250 0.1565 0.01623 0.00920 -0.0316 0.9581 1.0000
0.000 0.2197 0.01617 0.00903 -0.0385 0.9481 1.0000
0.250 0.2751 0.01603 0.00882 -0.0436 0.9362 1.0000
0.500 0.3194 0.01587 0.00862 -0.0463 0.9219 1.0000
0.750 0.3568 0.01567 0.00840 -0.0474 0.9064 1.0000
1.000 0.3838 0.01552 0.00823 -0.0463 0.8886 1.0000
1.250 0.4078 0.01533 0.00802 -0.0445 0.8697 1.0000
1.500 0.4301 0.01507 0.00774 -0.0421 0.8504 1.0000
1.750 0.4511 0.01474 0.00739 -0.0393 0.8307 1.0000
2.000 0.4700 0.01447 0.00710 -0.0362 0.8057 1.0000
2.250 0.4893 0.01416 0.00675 -0.0331 0.7781 1.0000
2.500 0.5088 0.01386 0.00638 -0.0300 0.7432 1.0000
2.750 0.5281 0.01365 0.00606 -0.0270 0.6894 1.0000
3.000 0.5464 0.01361 0.00562 -0.0237 0.5919 1.0000
3.250 0.5639 0.01433 0.00553 -0.0210 0.4780 1.0000
3.500 0.5844 0.01520 0.00587 -0.0196 0.4186 1.0000
3.750 0.6064 0.01594 0.00626 -0.0186 0.3841 1.0000
4.000 0.6293 0.01661 0.00673 -0.0177 0.3587 1.0000
4.250 0.6525 0.01730 0.00722 -0.0169 0.3391 1.0000
4.500 0.6762 0.01799 0.00775 -0.0162 0.3232 1.0000
4.750 0.7002 0.01867 0.00838 -0.0155 0.3096 1.0000
5.000 0.7244 0.01937 0.00904 -0.0149 0.2977 1.0000
5.250 0.7485 0.02011 0.00972 -0.0143 0.2871 1.0000
5.500 0.7728 0.02086 0.01037 -0.0137 0.2773 1.0000
5.750 0.7967 0.02158 0.01123 -0.0131 0.2680 1.0000
6.000 0.8215 0.02251 0.01202 -0.0126 0.2609 1.0000
6.250 0.8450 0.02329 0.01302 -0.0119 0.2535 1.0000
6.500 0.8694 0.02420 0.01388 -0.0114 0.2469 1.0000
6.750 0.8920 0.02508 0.01499 -0.0106 0.2396 1.0000
7.000 0.9156 0.02591 0.01580 -0.0100 0.2327 1.0000
7.250 0.9372 0.02683 0.01694 -0.0092 0.2251 1.0000
7.500 0.9603 0.02757 0.01767 -0.0086 0.2177 1.0000
7.750 0.9811 0.02867 0.01903 -0.0076 0.2111 1.0000
8.000 1.0033 0.02961 0.02007 -0.0069 0.2048 1.0000
8.250 1.0241 0.03082 0.02142 -0.0060 0.1986 1.0000
8.500 1.0443 0.03173 0.02254 -0.0050 0.1911 1.0000
8.750 1.0646 0.03289 0.02379 -0.0042 0.1845 1.0000
9.000 1.0826 0.03412 0.02530 -0.0029 0.1772 1.0000
9.250 1.1031 0.03537 0.02657 -0.0021 0.1708 1.0000
9.500 1.1183 0.03653 0.02804 -0.0006 0.1624 1.0000
9.750 1.1355 0.03764 0.02927 0.0006 0.1550 1.0000
10.000 1.1524 0.03850 0.03028 0.0019 0.1471 1.0000
10.250 1.1654 0.04013 0.03211 0.0034 0.1405 1.0000
10.500 1.1803 0.04122 0.03337 0.0049 0.1336 1.0000
10.750 1.1930 0.04274 0.03502 0.0064 0.1276 1.0000
11.000 1.2007 0.04437 0.03697 0.0084 0.1212 1.0000
11.250 1.2205 0.04537 0.03786 0.0091 0.1158 1.0000
11.500 1.2081 0.04877 0.04187 0.0126 0.1117 1.0000
11.750 1.2253 0.04915 0.04222 0.0138 0.1059 1.0000
12.000 1.2278 0.05145 0.04465 0.0157 0.1020 1.0000
12.250 1.2026 0.05544 0.04909 0.0194 0.1003 1.0000
12.500 1.1722 0.05965 0.05360 0.0226 0.0995 1.0000
12.750 1.1349 0.06524 0.05946 0.0237 0.0996 1.0000
13.000 1.0892 0.07305 0.06748 0.0220 0.1008 1.0000
13.250 1.0407 0.08331 0.07787 0.0171 0.1024 1.0000
13.500 0.7711 0.15492 0.14897 -0.0300 0.1644 1.0000
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Polar data table (+)
Polar graphs
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