BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 50,000 Max Cl/Cd: 24.32 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr9-il-50000.txt Download as CSV file: xf-vr9-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-9 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6638 0.12250 0.11579 0.0246 1.0000 0.2142
-9.250 -0.6424 0.11658 0.10985 0.0267 1.0000 0.2320
-9.000 -0.6580 0.11517 0.10855 0.0242 1.0000 0.2416
-8.750 -0.6348 0.10937 0.10271 0.0264 1.0000 0.2594
-8.500 -0.6283 0.10569 0.09907 0.0267 1.0000 0.2758
-8.250 -0.6294 0.10271 0.09615 0.0267 1.0000 0.2939
-8.000 -0.6406 0.10058 0.09406 0.0260 1.0000 0.3098
-7.750 -0.6212 0.09602 0.08949 0.0282 1.0000 0.3356
-7.500 -0.6093 0.09217 0.08566 0.0299 1.0000 0.3615
-7.250 -0.6023 0.08886 0.08239 0.0315 1.0000 0.3893
-7.000 -0.6029 0.08622 0.07983 0.0334 1.0000 0.4187
-6.750 -0.5863 0.08212 0.07574 0.0353 1.0000 0.4484
-6.500 -0.5636 0.07812 0.07172 0.0382 1.0000 0.4919
-5.250 -0.5509 0.04272 0.03403 -0.0150 1.0000 0.1308
-5.000 -0.5255 0.03853 0.02922 -0.0146 1.0000 0.1159
-4.750 -0.5010 0.03505 0.02521 -0.0139 1.0000 0.1120
-4.500 -0.4755 0.03213 0.02180 -0.0131 1.0000 0.1125
-4.250 -0.4474 0.02934 0.01841 -0.0121 1.0000 0.1092
-4.000 -0.4187 0.02695 0.01556 -0.0110 1.0000 0.1082
-3.750 -0.3902 0.02473 0.01318 -0.0100 1.0000 0.1108
-3.500 -0.3631 0.02290 0.01129 -0.0090 1.0000 0.1233
-3.250 -0.3355 0.02134 0.00951 -0.0078 1.0000 0.1337
-3.000 -0.3106 0.01981 0.00801 -0.0067 1.0000 0.1493
-2.750 -0.1933 0.01555 0.00654 -0.0148 1.0000 1.0000
-2.500 -0.1772 0.01512 0.00578 -0.0138 1.0000 1.0000
-2.250 -0.1604 0.01478 0.00515 -0.0127 1.0000 1.0000
-2.000 -0.1426 0.01452 0.00457 -0.0116 1.0000 1.0000
-1.750 -0.1241 0.01432 0.00415 -0.0105 1.0000 1.0000
-1.500 -0.1050 0.01417 0.00380 -0.0094 1.0000 1.0000
-1.250 -0.0853 0.01406 0.00352 -0.0083 1.0000 1.0000
-1.000 -0.0654 0.01398 0.00331 -0.0072 1.0000 1.0000
-0.750 -0.0454 0.01393 0.00315 -0.0061 1.0000 1.0000
-0.500 -0.0253 0.01390 0.00299 -0.0050 1.0000 1.0000
-0.250 -0.0052 0.01389 0.00293 -0.0039 1.0000 1.0000
0.000 0.0149 0.01390 0.00291 -0.0027 1.0000 1.0000
0.250 0.0349 0.01394 0.00295 -0.0016 1.0000 1.0000
0.500 0.0546 0.01400 0.00303 -0.0005 1.0000 1.0000
0.750 0.0742 0.01409 0.00318 0.0005 1.0000 1.0000
1.000 0.0932 0.01422 0.00339 0.0016 1.0000 1.0000
1.250 0.1116 0.01440 0.00364 0.0027 1.0000 1.0000
1.500 0.1292 0.01463 0.00397 0.0039 1.0000 1.0000
1.750 0.1460 0.01492 0.00438 0.0049 1.0000 1.0000
2.000 0.1622 0.01529 0.00485 0.0059 1.0000 1.0000
2.250 0.1780 0.01572 0.00542 0.0068 1.0000 1.0000
2.500 0.1935 0.01621 0.00614 0.0075 1.0000 1.0000
2.750 0.2089 0.01679 0.00688 0.0081 1.0000 1.0000
3.000 0.3886 0.01598 0.00772 -0.0145 0.8415 1.0000
3.250 0.3927 0.01672 0.00697 -0.0021 0.4100 1.0000
3.500 0.4053 0.02020 0.00850 0.0000 0.1604 1.0000
3.750 0.4298 0.02184 0.01010 0.0011 0.1365 1.0000
4.000 0.4547 0.02350 0.01170 0.0021 0.1187 1.0000
4.250 0.4828 0.02529 0.01365 0.0034 0.1120 1.0000
4.500 0.5115 0.02763 0.01606 0.0044 0.1084 1.0000
4.750 0.5400 0.03037 0.01907 0.0054 0.1076 1.0000
5.000 0.5664 0.03300 0.02235 0.0064 0.1045 1.0000
5.250 0.5915 0.03598 0.02590 0.0073 0.1033 1.0000
5.500 0.6156 0.04014 0.03026 0.0080 0.1069 1.0000
5.750 0.6391 0.04395 0.03509 0.0089 0.1187 1.0000
6.000 0.6610 0.04904 0.04119 0.0086 0.1408 1.0000
6.250 0.6858 0.05667 0.04942 0.0065 0.1881 1.0000
7.000 0.6292 0.08425 0.07775 -0.0404 0.4459 1.0000
7.250 0.6371 0.08765 0.08113 -0.0390 0.4214 1.0000
7.500 0.6348 0.09044 0.08384 -0.0380 0.3993 1.0000
7.750 0.6536 0.09501 0.08843 -0.0369 0.3798 1.0000
8.000 0.6475 0.09761 0.09102 -0.0363 0.3586 1.0000
8.250 0.6753 0.10323 0.09670 -0.0345 0.3378 1.0000
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Polar data table (+)
Polar graphs
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