BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL V23010-1.58 AIRFOIL (v23010-il) Reynolds number: 100,000 Max Cl/Cd: 35.12 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v23010-il-100000.txt Download as CSV file: xf-v23010-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING-VERTOL V23010-1.58 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5064 0.10016 0.09495 -0.0064 1.0000 0.1003
-9.000 -0.5305 0.09574 0.09063 -0.0142 1.0000 0.1027
-8.750 -0.5644 0.09142 0.08632 -0.0204 1.0000 0.1032
-8.500 -0.5193 0.08745 0.08243 -0.0140 1.0000 0.1070
-8.250 -0.5101 0.08467 0.07967 -0.0132 1.0000 0.1112
-8.000 -0.5236 0.08029 0.07535 -0.0169 1.0000 0.1146
-7.750 -0.5535 0.07613 0.07107 -0.0216 1.0000 0.1180
-7.500 -0.5604 0.07139 0.06628 -0.0225 1.0000 0.1210
-7.250 -0.5362 0.06886 0.06391 -0.0201 1.0000 0.1269
-6.750 -0.5371 0.06181 0.05674 -0.0206 1.0000 0.1402
-6.500 -0.5437 0.05910 0.05372 -0.0208 1.0000 0.1524
-6.250 -0.5242 0.05608 0.05094 -0.0191 1.0000 0.1588
-6.000 -0.5186 0.05332 0.04813 -0.0181 1.0000 0.1725
-5.750 -0.5105 0.05093 0.04573 -0.0166 1.0000 0.1887
-5.500 -0.5012 0.04885 0.04369 -0.0147 1.0000 0.2077
-5.250 -0.4948 0.04690 0.04180 -0.0123 1.0000 0.2355
-4.750 -0.4772 0.04402 0.03917 -0.0060 1.0000 0.2982
-4.500 -0.4652 0.04337 0.03880 -0.0008 1.0000 0.3362
-4.250 -0.4569 0.04347 0.03918 0.0063 1.0000 0.3883
-3.000 -0.3355 0.02750 0.01897 0.0014 1.0000 0.1202
-2.750 -0.3146 0.02535 0.01682 0.0027 1.0000 0.1095
-2.500 -0.2940 0.02472 0.01590 0.0046 1.0000 0.1004
-2.250 -0.2740 0.02351 0.01458 0.0060 1.0000 0.0955
-2.000 -0.2198 0.02265 0.01335 0.0018 0.9888 0.0901
-1.750 -0.1678 0.02127 0.01199 -0.0026 0.9771 0.0910
-1.500 -0.1165 0.02024 0.01095 -0.0065 0.9648 0.0903
-1.250 -0.0661 0.01908 0.00993 -0.0104 0.9525 0.0909
-1.000 -0.0153 0.01794 0.00899 -0.0142 0.9400 0.0934
-0.750 0.0310 0.01710 0.00819 -0.0171 0.9245 0.1000
-0.500 0.0700 0.01631 0.00740 -0.0185 0.9055 0.1097
-0.250 0.1073 0.01557 0.00669 -0.0193 0.8843 0.1289
0.000 0.2663 0.01290 0.00679 -0.0381 0.8682 1.0000
0.250 0.2901 0.01273 0.00641 -0.0367 0.8255 1.0000
0.500 0.3093 0.01263 0.00608 -0.0344 0.7799 1.0000
0.750 0.3273 0.01264 0.00581 -0.0319 0.7316 1.0000
1.000 0.3437 0.01274 0.00563 -0.0291 0.6719 1.0000
1.250 0.3599 0.01294 0.00543 -0.0264 0.6051 1.0000
1.500 0.3773 0.01332 0.00533 -0.0241 0.5475 1.0000
1.750 0.3964 0.01374 0.00540 -0.0224 0.5044 1.0000
2.000 0.4169 0.01415 0.00553 -0.0209 0.4756 1.0000
2.250 0.4382 0.01456 0.00570 -0.0197 0.4540 1.0000
2.500 0.4602 0.01497 0.00592 -0.0186 0.4368 1.0000
2.750 0.4828 0.01539 0.00620 -0.0175 0.4222 1.0000
3.000 0.5054 0.01582 0.00651 -0.0165 0.4085 1.0000
3.250 0.5281 0.01625 0.00682 -0.0156 0.3956 1.0000
3.500 0.5512 0.01674 0.00711 -0.0147 0.3842 1.0000
3.750 0.5743 0.01714 0.00755 -0.0137 0.3729 1.0000
4.000 0.5978 0.01765 0.00799 -0.0129 0.3634 1.0000
4.250 0.6213 0.01815 0.00843 -0.0121 0.3542 1.0000
4.500 0.6449 0.01871 0.00900 -0.0113 0.3456 1.0000
4.750 0.6687 0.01926 0.00950 -0.0105 0.3371 1.0000
5.000 0.6918 0.01984 0.01015 -0.0097 0.3280 1.0000
5.250 0.7158 0.02044 0.01064 -0.0090 0.3195 1.0000
5.500 0.7383 0.02103 0.01139 -0.0081 0.3099 1.0000
5.750 0.7628 0.02177 0.01198 -0.0074 0.3022 1.0000
6.000 0.7848 0.02244 0.01288 -0.0065 0.2929 1.0000
6.250 0.8091 0.02328 0.01361 -0.0059 0.2855 1.0000
6.500 0.8306 0.02405 0.01462 -0.0049 0.2763 1.0000
6.750 0.8546 0.02494 0.01543 -0.0043 0.2691 1.0000
7.000 0.8754 0.02588 0.01664 -0.0033 0.2609 1.0000
7.250 0.8995 0.02682 0.01754 -0.0027 0.2549 1.0000
7.500 0.9188 0.02806 0.01910 -0.0016 0.2479 1.0000
7.750 0.9413 0.02896 0.02007 -0.0009 0.2414 1.0000
8.000 0.9633 0.03019 0.02135 -0.0002 0.2360 1.0000
8.250 0.9806 0.03144 0.02297 0.0011 0.2290 1.0000
8.500 1.0070 0.03178 0.02311 0.0014 0.2220 1.0000
8.750 1.0224 0.03258 0.02426 0.0029 0.2126 1.0000
9.000 1.0469 0.03253 0.02407 0.0035 0.2042 1.0000
9.250 1.0652 0.03295 0.02472 0.0048 0.1953 1.0000
9.500 1.0860 0.03336 0.02517 0.0057 0.1878 1.0000
9.750 1.1069 0.03335 0.02524 0.0068 0.1790 1.0000
10.000 1.1232 0.03389 0.02599 0.0082 0.1699 1.0000
10.250 1.1453 0.03355 0.02556 0.0092 0.1604 1.0000
10.500 1.1654 0.03320 0.02511 0.0104 0.1493 1.0000
10.750 1.1783 0.03355 0.02553 0.0123 0.1368 1.0000
11.000 1.1890 0.03439 0.02642 0.0142 0.1243 1.0000
11.250 1.1959 0.03595 0.02814 0.0164 0.1136 1.0000
11.500 1.2027 0.03776 0.03004 0.0184 0.1053 1.0000
11.750 1.2178 0.03900 0.03107 0.0195 0.0979 1.0000
12.000 1.2138 0.04139 0.03389 0.0222 0.0933 1.0000
12.250 1.2177 0.04306 0.03566 0.0242 0.0889 1.0000
12.500 1.2257 0.04495 0.03749 0.0257 0.0851 1.0000
12.750 1.2120 0.04758 0.04046 0.0285 0.0830 1.0000
13.000 1.1998 0.05056 0.04369 0.0301 0.0812 1.0000
13.250 1.1898 0.05354 0.04685 0.0308 0.0793 1.0000
13.500 1.1899 0.05606 0.04941 0.0312 0.0772 1.0000
13.750 1.1939 0.05890 0.05222 0.0314 0.0751 1.0000
14.000 1.1682 0.06417 0.05777 0.0298 0.0749 1.0000
14.250 1.1400 0.07057 0.06441 0.0268 0.0749 1.0000
14.500 1.1079 0.07840 0.07246 0.0221 0.0752 1.0000
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Polar data table (+)
Polar graphs
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