BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: BOEING-VERTOL VR-15 AIRFOIL (vr15-il) Reynolds number: 1,000,000 Max Cl/Cd: 81.73 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr15-il-1000000-n5.txt Download as CSV file: xf-vr15-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-15 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -1.0188 0.02819 0.02487 -0.0093 1.0000 0.0030
-10.250 -1.0067 0.02509 0.02143 -0.0079 1.0000 0.0030
-10.000 -0.9897 0.02297 0.01904 -0.0068 1.0000 0.0030
-9.750 -0.9703 0.02130 0.01714 -0.0059 1.0000 0.0031
-9.500 -0.9493 0.01992 0.01557 -0.0051 1.0000 0.0031
-9.250 -0.9270 0.01875 0.01422 -0.0044 1.0000 0.0031
-9.000 -0.9039 0.01773 0.01305 -0.0039 1.0000 0.0031
-8.750 -0.8808 0.01665 0.01181 -0.0033 1.0000 0.0032
-8.500 -0.8568 0.01570 0.01072 -0.0028 1.0000 0.0033
-8.000 -0.8033 0.01419 0.00898 -0.0028 0.9843 0.0037
-7.750 -0.7770 0.01358 0.00829 -0.0026 0.9764 0.0040
-7.500 -0.7517 0.01306 0.00769 -0.0021 0.9694 0.0043
-7.250 -0.7275 0.01260 0.00715 -0.0014 0.9621 0.0047
-7.000 -0.7036 0.01218 0.00666 -0.0005 0.9557 0.0051
-6.750 -0.6791 0.01172 0.00617 0.0002 0.9493 0.0061
-6.500 -0.6549 0.01137 0.00575 0.0010 0.9433 0.0071
-6.250 -0.6294 0.01103 0.00539 0.0015 0.9371 0.0083
-6.000 -0.6043 0.01074 0.00506 0.0021 0.9306 0.0094
-5.750 -0.5784 0.01047 0.00474 0.0026 0.9245 0.0103
-5.500 -0.5525 0.01025 0.00452 0.0030 0.9179 0.0116
-5.250 -0.5264 0.01005 0.00429 0.0035 0.9117 0.0127
-5.000 -0.5000 0.00984 0.00405 0.0038 0.9045 0.0137
-4.750 -0.4736 0.00967 0.00387 0.0042 0.8981 0.0148
-4.500 -0.4466 0.00954 0.00374 0.0045 0.8907 0.0161
-4.250 -0.4199 0.00942 0.00358 0.0048 0.8830 0.0174
-4.000 -0.3926 0.00934 0.00348 0.0050 0.8746 0.0184
-3.750 -0.3660 0.00911 0.00320 0.0053 0.8670 0.0196
-3.500 -0.3390 0.00891 0.00300 0.0056 0.8588 0.0211
-3.250 -0.3118 0.00876 0.00282 0.0058 0.8494 0.0221
-3.000 -0.2849 0.00862 0.00263 0.0061 0.8352 0.0232
-2.750 -0.2580 0.00849 0.00242 0.0064 0.8169 0.0239
-2.500 -0.2310 0.00837 0.00222 0.0067 0.7995 0.0245
-2.250 -0.2037 0.00828 0.00204 0.0069 0.7826 0.0250
-2.000 -0.1764 0.00816 0.00186 0.0071 0.7646 0.0258
-1.750 -0.1491 0.00803 0.00165 0.0073 0.7471 0.0272
-1.500 -0.1215 0.00793 0.00151 0.0075 0.7300 0.0291
-1.250 -0.0938 0.00786 0.00139 0.0076 0.7131 0.0313
-1.000 -0.0660 0.00780 0.00128 0.0076 0.6963 0.0333
-0.750 -0.0382 0.00775 0.00119 0.0077 0.6744 0.0388
-0.500 -0.0106 0.00773 0.00110 0.0078 0.6462 0.0481
-0.250 0.0163 0.00765 0.00103 0.0079 0.6052 0.0920
0.000 0.0422 0.00758 0.00099 0.0081 0.5428 0.1734
0.250 0.0668 0.00747 0.00097 0.0084 0.4638 0.2977
0.500 0.0896 0.00709 0.00095 0.0090 0.3983 0.4875
0.750 0.1043 0.00615 0.00092 0.0115 0.3513 0.7959
1.000 0.1567 0.00613 0.00122 0.0063 0.3046 0.9634
1.250 0.1956 0.00643 0.00139 0.0040 0.2766 0.9793
1.500 0.2298 0.00664 0.00150 0.0026 0.2571 0.9852
1.750 0.2665 0.00680 0.00157 0.0005 0.2388 0.9876
2.000 0.3001 0.00696 0.00163 -0.0008 0.2209 0.9896
2.250 0.3315 0.00712 0.00170 -0.0017 0.2035 0.9913
2.500 0.3625 0.00727 0.00177 -0.0025 0.1896 0.9930
2.750 0.3931 0.00739 0.00185 -0.0031 0.1803 0.9944
3.000 0.4252 0.00751 0.00191 -0.0042 0.1711 0.9951
3.250 0.4567 0.00763 0.00198 -0.0051 0.1622 0.9959
3.500 0.4879 0.00774 0.00207 -0.0059 0.1549 0.9967
3.750 0.5189 0.00788 0.00217 -0.0067 0.1469 0.9975
4.000 0.5498 0.00800 0.00226 -0.0075 0.1402 0.9983
4.250 0.5807 0.00816 0.00239 -0.0083 0.1313 0.9991
4.500 0.6118 0.00829 0.00251 -0.0091 0.1258 0.9998
4.750 0.6393 0.00847 0.00264 -0.0092 0.1172 1.0000
5.000 0.6648 0.00864 0.00277 -0.0088 0.1080 1.0000
5.250 0.6904 0.00880 0.00292 -0.0084 0.1019 1.0000
5.500 0.7158 0.00900 0.00309 -0.0081 0.0937 1.0000
5.750 0.7411 0.00918 0.00325 -0.0076 0.0874 1.0000
6.000 0.7662 0.00943 0.00345 -0.0072 0.0761 1.0000
6.250 0.7908 0.00974 0.00370 -0.0068 0.0619 1.0000
6.500 0.8155 0.01004 0.00396 -0.0063 0.0531 1.0000
6.750 0.8401 0.01033 0.00423 -0.0058 0.0475 1.0000
7.000 0.8647 0.01060 0.00449 -0.0053 0.0429 1.0000
7.250 0.8892 0.01088 0.00478 -0.0048 0.0376 1.0000
7.500 0.9132 0.01123 0.00511 -0.0042 0.0318 1.0000
7.750 0.9370 0.01160 0.00545 -0.0036 0.0270 1.0000
8.000 0.9610 0.01192 0.00579 -0.0031 0.0241 1.0000
8.250 0.9847 0.01229 0.00617 -0.0025 0.0215 1.0000
8.500 1.0081 0.01269 0.00659 -0.0018 0.0189 1.0000
8.750 1.0318 0.01301 0.00695 -0.0012 0.0181 1.0000
9.000 1.0552 0.01337 0.00735 -0.0005 0.0170 1.0000
9.250 1.0782 0.01378 0.00778 0.0002 0.0158 1.0000
9.500 1.1006 0.01425 0.00828 0.0009 0.0144 1.0000
9.750 1.1230 0.01471 0.00879 0.0017 0.0135 1.0000
10.000 1.1457 0.01511 0.00925 0.0024 0.0130 1.0000
10.250 1.1679 0.01555 0.00974 0.0031 0.0124 1.0000
10.500 1.1898 0.01603 0.01027 0.0039 0.0118 1.0000
10.750 1.2111 0.01654 0.01083 0.0047 0.0112 1.0000
11.000 1.2319 0.01711 0.01146 0.0057 0.0106 1.0000
11.250 1.2512 0.01783 0.01225 0.0067 0.0098 1.0000
11.500 1.2717 0.01837 0.01286 0.0076 0.0095 1.0000
11.750 1.2921 0.01888 0.01343 0.0086 0.0091 1.0000
12.000 1.3119 0.01943 0.01404 0.0095 0.0087 1.0000
12.250 1.3309 0.02003 0.01470 0.0105 0.0082 1.0000
12.500 1.3492 0.02069 0.01542 0.0116 0.0078 1.0000
12.750 1.3665 0.02142 0.01623 0.0128 0.0075 1.0000
13.000 1.3825 0.02225 0.01714 0.0141 0.0072 1.0000
13.250 1.3962 0.02325 0.01823 0.0157 0.0068 1.0000
13.500 1.4108 0.02410 0.01918 0.0171 0.0067 1.0000
13.750 1.4246 0.02496 0.02013 0.0185 0.0065 1.0000
14.000 1.4362 0.02589 0.02117 0.0202 0.0064 1.0000
14.250 1.4434 0.02688 0.02225 0.0225 0.0062 1.0000
14.500 1.4492 0.02802 0.02350 0.0246 0.0061 1.0000
14.750 1.4544 0.02933 0.02492 0.0263 0.0059 1.0000
15.000 1.4586 0.03085 0.02654 0.0278 0.0058 1.0000
15.250 1.4614 0.03260 0.02842 0.0289 0.0057 1.0000
15.500 1.4628 0.03464 0.03056 0.0297 0.0055 1.0000
15.750 1.4624 0.03704 0.03308 0.0300 0.0054 1.0000
16.000 1.4594 0.03996 0.03612 0.0297 0.0052 1.0000
16.250 1.4530 0.04358 0.03986 0.0288 0.0051 1.0000
16.500 1.4419 0.04828 0.04471 0.0268 0.0050 1.0000
16.750 1.4236 0.05477 0.05137 0.0230 0.0050 1.0000
17.000 1.3912 0.06502 0.06186 0.0163 0.0051 1.0000
17.250 1.3282 0.08163 0.07877 0.0065 0.0054 1.0000
17.500 1.2526 0.09917 0.09651 -0.0026 0.0057 1.0000
|
Polar data table (+)
Polar graphs
<< Back to BOEING-VERTOL VR-15 AIRFOIL (vr15-il)