BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-11X AIRFOIL (vr11x-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.55 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-vr11x-il-1000000-n5.txt Download as CSV file: xf-vr11x-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL VR-11X 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4985 0.08255 0.08047 -0.0230 0.8458 0.0067
-8.750 -0.5077 0.07560 0.07354 -0.0309 0.8448 0.0067
-8.500 -0.5230 0.06907 0.06695 -0.0354 0.8437 0.0066
-8.250 -0.5285 0.06320 0.06098 -0.0381 0.8428 0.0067
-8.000 -0.5305 0.05766 0.05531 -0.0394 0.8420 0.0067
-7.750 -0.5299 0.05221 0.04969 -0.0397 0.8412 0.0067
-7.500 -0.5264 0.04696 0.04424 -0.0391 0.8405 0.0067
-7.250 -0.5220 0.04139 0.03841 -0.0377 0.8398 0.0067
-7.000 -0.5166 0.03564 0.03231 -0.0355 0.8389 0.0066
-6.750 -0.5447 0.01857 0.01356 -0.0260 0.8376 0.0064
-6.500 -0.5224 0.01707 0.01183 -0.0250 0.8368 0.0064
-6.250 -0.4984 0.01601 0.01059 -0.0243 0.8360 0.0065
-6.000 -0.4732 0.01516 0.00961 -0.0238 0.8354 0.0066
-5.750 -0.4477 0.01439 0.00874 -0.0233 0.8348 0.0067
-5.500 -0.4219 0.01372 0.00798 -0.0229 0.8343 0.0068
-5.250 -0.3957 0.01314 0.00733 -0.0226 0.8338 0.0070
-5.000 -0.3695 0.01261 0.00673 -0.0222 0.8334 0.0072
-4.750 -0.3431 0.01213 0.00619 -0.0219 0.8325 0.0074
-4.500 -0.3166 0.01168 0.00569 -0.0216 0.8306 0.0077
-4.250 -0.2902 0.01129 0.00525 -0.0212 0.8278 0.0078
-4.000 -0.2635 0.01095 0.00486 -0.0208 0.8255 0.0080
-3.750 -0.2371 0.01059 0.00446 -0.0205 0.8241 0.0082
-3.500 -0.2111 0.01021 0.00404 -0.0200 0.8218 0.0085
-3.250 -0.1836 0.00989 0.00374 -0.0199 0.8186 0.0088
-3.000 -0.1560 0.00963 0.00347 -0.0198 0.8154 0.0091
-2.750 -0.1286 0.00938 0.00321 -0.0196 0.8122 0.0094
-2.500 -0.1012 0.00913 0.00294 -0.0194 0.8085 0.0098
-2.250 -0.0733 0.00891 0.00272 -0.0193 0.8036 0.0103
-2.000 -0.0453 0.00869 0.00250 -0.0192 0.7973 0.0109
-1.750 -0.0176 0.00846 0.00226 -0.0191 0.7902 0.0119
-1.500 0.0105 0.00827 0.00206 -0.0191 0.7787 0.0129
-1.250 0.0382 0.00811 0.00181 -0.0189 0.7433 0.0140
-1.000 0.0634 0.00872 0.00177 -0.0187 0.5816 0.0159
-0.750 0.0904 0.00885 0.00175 -0.0186 0.5414 0.0193
-0.500 0.1170 0.00893 0.00173 -0.0185 0.4964 0.0335
-0.250 0.1421 0.00897 0.00173 -0.0182 0.4430 0.0854
0.000 0.1651 0.00876 0.00171 -0.0175 0.3983 0.2111
0.250 0.1817 0.00801 0.00168 -0.0158 0.3577 0.4910
0.500 0.1965 0.00742 0.00169 -0.0132 0.3287 0.7037
1.000 0.3108 0.00751 0.00222 -0.0265 0.2520 0.9650
1.250 0.3408 0.00782 0.00235 -0.0271 0.2220 0.9732
1.500 0.3719 0.00805 0.00246 -0.0279 0.2027 0.9766
1.750 0.4045 0.00823 0.00255 -0.0291 0.1905 0.9786
2.000 0.4360 0.00840 0.00264 -0.0300 0.1819 0.9808
2.250 0.4660 0.00855 0.00273 -0.0306 0.1762 0.9834
2.500 0.4947 0.00869 0.00283 -0.0309 0.1720 0.9860
2.750 0.5273 0.00885 0.00292 -0.0321 0.1672 0.9871
3.000 0.5594 0.00899 0.00303 -0.0332 0.1625 0.9883
3.250 0.5912 0.00911 0.00312 -0.0342 0.1604 0.9897
3.500 0.6224 0.00924 0.00323 -0.0351 0.1580 0.9912
3.750 0.6535 0.00939 0.00336 -0.0359 0.1556 0.9928
4.000 0.6847 0.00957 0.00350 -0.0369 0.1526 0.9946
4.250 0.7192 0.00975 0.00363 -0.0386 0.1477 0.9957
4.500 0.7539 0.00986 0.00375 -0.0403 0.1456 0.9969
4.750 0.7878 0.00999 0.00386 -0.0418 0.1424 0.9982
5.000 0.8207 0.01015 0.00399 -0.0432 0.1394 0.9992
5.250 0.8520 0.01031 0.00412 -0.0442 0.1359 0.9999
5.500 0.8773 0.01048 0.00428 -0.0439 0.1323 1.0000
5.750 0.9017 0.01060 0.00440 -0.0433 0.1302 1.0000
6.000 0.9258 0.01075 0.00454 -0.0428 0.1274 1.0000
6.250 0.9496 0.01092 0.00470 -0.0421 0.1239 1.0000
6.500 0.9731 0.01111 0.00487 -0.0415 0.1197 1.0000
6.750 0.9967 0.01128 0.00504 -0.0408 0.1168 1.0000
7.000 1.0201 0.01145 0.00522 -0.0401 0.1133 1.0000
7.250 1.0429 0.01168 0.00541 -0.0393 0.1081 1.0000
7.500 1.0657 0.01190 0.00562 -0.0385 0.1033 1.0000
7.750 1.0875 0.01219 0.00586 -0.0376 0.0950 1.0000
8.000 1.1088 0.01250 0.00613 -0.0366 0.0855 1.0000
8.250 1.1294 0.01287 0.00644 -0.0355 0.0760 1.0000
8.500 1.1495 0.01326 0.00679 -0.0343 0.0676 1.0000
8.750 1.1694 0.01366 0.00715 -0.0331 0.0611 1.0000
9.000 1.1890 0.01405 0.00752 -0.0318 0.0553 1.0000
9.250 1.2086 0.01442 0.00789 -0.0306 0.0504 1.0000
9.500 1.2273 0.01486 0.00830 -0.0291 0.0448 1.0000
9.750 1.2449 0.01536 0.00877 -0.0276 0.0368 1.0000
10.000 1.2591 0.01613 0.00944 -0.0255 0.0232 1.0000
10.250 1.2763 0.01662 0.00993 -0.0239 0.0205 1.0000
10.500 1.2940 0.01704 0.01039 -0.0224 0.0196 1.0000
10.750 1.3109 0.01747 0.01085 -0.0207 0.0190 1.0000
11.000 1.3244 0.01791 0.01132 -0.0184 0.0186 1.0000
11.250 1.3372 0.01835 0.01181 -0.0160 0.0182 1.0000
11.500 1.3504 0.01884 0.01233 -0.0137 0.0177 1.0000
11.750 1.3639 0.01935 0.01290 -0.0116 0.0174 1.0000
12.000 1.3772 0.01993 0.01352 -0.0096 0.0168 1.0000
12.250 1.3910 0.02050 0.01415 -0.0077 0.0165 1.0000
12.500 1.4052 0.02107 0.01477 -0.0059 0.0163 1.0000
12.750 1.4191 0.02167 0.01544 -0.0042 0.0161 1.0000
13.000 1.4325 0.02233 0.01616 -0.0025 0.0159 1.0000
13.250 1.4455 0.02302 0.01691 -0.0008 0.0157 1.0000
13.500 1.4581 0.02376 0.01772 0.0009 0.0155 1.0000
13.750 1.4700 0.02455 0.01858 0.0026 0.0152 1.0000
14.000 1.4812 0.02541 0.01950 0.0043 0.0150 1.0000
14.250 1.4916 0.02634 0.02050 0.0060 0.0147 1.0000
14.500 1.5011 0.02734 0.02158 0.0077 0.0145 1.0000
14.750 1.5096 0.02843 0.02275 0.0094 0.0143 1.0000
15.000 1.5170 0.02963 0.02402 0.0112 0.0141 1.0000
15.250 1.5227 0.03097 0.02544 0.0129 0.0138 1.0000
15.500 1.5268 0.03246 0.02702 0.0147 0.0136 1.0000
15.750 1.5289 0.03417 0.02882 0.0164 0.0133 1.0000
16.000 1.5278 0.03621 0.03097 0.0182 0.0130 1.0000
16.250 1.5334 0.03774 0.03258 0.0193 0.0129 1.0000
16.500 1.5375 0.03947 0.03440 0.0203 0.0127 1.0000
16.750 1.5392 0.04151 0.03654 0.0213 0.0126 1.0000
17.000 1.5395 0.04383 0.03897 0.0219 0.0125 1.0000
17.250 1.5382 0.04649 0.04173 0.0223 0.0124 1.0000
17.500 1.5350 0.04959 0.04494 0.0222 0.0122 1.0000
17.750 1.5296 0.05323 0.04871 0.0216 0.0121 1.0000
18.000 1.5208 0.05759 0.05319 0.0205 0.0120 1.0000
18.250 1.5078 0.06286 0.05861 0.0186 0.0118 1.0000
18.500 1.4881 0.06951 0.06542 0.0158 0.0118 1.0000
18.750 1.4576 0.07828 0.07439 0.0117 0.0118 1.0000
19.000 1.4095 0.09047 0.08680 0.0060 0.0120 1.0000
19.250 1.3406 0.10632 0.10289 -0.0012 0.0123 1.0000
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Polar data table (+)
Polar graphs
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