BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 500,000 Max Cl/Cd: 39.8 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr9-il-500000.txt Download as CSV file: xf-vr9-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6348 0.08719 0.08499 0.0065 1.0000 0.0105
-8.250 -0.6374 0.08266 0.08049 0.0036 1.0000 0.0106
-8.000 -0.6442 0.07791 0.07578 -0.0003 1.0000 0.0109
-7.750 -0.6475 0.07254 0.07039 -0.0054 1.0000 0.0108
-7.500 -0.6462 0.06721 0.06500 -0.0092 1.0000 0.0110
-7.250 -0.6419 0.06204 0.05973 -0.0118 1.0000 0.0114
-7.000 -0.6339 0.05705 0.05459 -0.0137 1.0000 0.0120
-6.750 -0.6194 0.05261 0.04996 -0.0145 1.0000 0.0130
-6.500 -0.6020 0.04862 0.04573 -0.0145 1.0000 0.0135
-6.250 -0.5877 0.04445 0.04130 -0.0142 1.0000 0.0136
-6.000 -0.5725 0.04036 0.03693 -0.0137 1.0000 0.0137
-5.750 -0.5561 0.03653 0.03279 -0.0129 1.0000 0.0137
-5.500 -0.5380 0.03333 0.02924 -0.0119 1.0000 0.0138
-5.250 -0.5188 0.03031 0.02587 -0.0109 1.0000 0.0138
-5.000 -0.5050 0.02374 0.01881 -0.0097 1.0000 0.0146
-4.750 -0.4837 0.02099 0.01577 -0.0088 1.0000 0.0152
-4.500 -0.4607 0.01891 0.01348 -0.0079 1.0000 0.0157
-4.250 -0.4371 0.01708 0.01145 -0.0070 1.0000 0.0167
-4.000 -0.4127 0.01539 0.00955 -0.0060 1.0000 0.0179
-3.750 -0.3880 0.01378 0.00774 -0.0049 1.0000 0.0194
-3.500 -0.3632 0.01289 0.00670 -0.0039 1.0000 0.0218
-3.250 -0.3412 0.01108 0.00479 -0.0025 1.0000 0.0231
-3.000 -0.3186 0.01005 0.00366 -0.0013 1.0000 0.0241
-2.750 -0.2952 0.00939 0.00295 -0.0004 1.0000 0.0263
-2.500 -0.2596 0.00890 0.00242 -0.0021 0.9903 0.0296
-2.250 -0.2005 0.00847 0.00176 -0.0088 0.8946 0.0325
-2.000 -0.1796 0.00871 0.00149 -0.0068 0.7656 0.0353
-1.750 -0.1551 0.00881 0.00126 -0.0060 0.7017 0.0383
-1.500 -0.1296 0.00890 0.00107 -0.0055 0.6473 0.0399
-1.250 -0.1033 0.00893 0.00091 -0.0052 0.6097 0.0405
-1.000 -0.0765 0.00895 0.00079 -0.0050 0.5813 0.0406
-0.750 -0.0495 0.00896 0.00071 -0.0048 0.5564 0.0406
-0.500 -0.0226 0.00900 0.00063 -0.0046 0.5297 0.0407
-0.250 -0.0017 0.01038 0.00072 -0.0041 0.1454 0.0408
0.000 0.0246 0.01067 0.00073 -0.0040 0.0521 0.0415
0.250 0.0518 0.01069 0.00073 -0.0039 0.0492 0.0430
0.500 0.0790 0.01070 0.00075 -0.0038 0.0472 0.0469
0.750 0.1062 0.01068 0.00081 -0.0037 0.0463 0.0606
1.000 0.1246 0.00886 0.00079 -0.0028 0.0460 0.6320
1.250 0.1492 0.00863 0.00088 -0.0021 0.0457 0.7133
1.500 0.1702 0.00824 0.00101 -0.0004 0.0454 0.8392
1.750 0.2151 0.00814 0.00124 -0.0037 0.0425 0.9707
2.000 0.2655 0.00828 0.00147 -0.0088 0.0399 1.0000
2.250 0.2907 0.00843 0.00166 -0.0082 0.0358 1.0000
2.500 0.3157 0.00866 0.00191 -0.0076 0.0313 1.0000
2.750 0.3406 0.00896 0.00225 -0.0069 0.0299 1.0000
3.000 0.3653 0.00936 0.00273 -0.0062 0.0294 1.0000
3.250 0.3898 0.00981 0.00325 -0.0056 0.0276 1.0000
3.500 0.4139 0.01040 0.00390 -0.0048 0.0266 1.0000
3.750 0.4372 0.01125 0.00481 -0.0038 0.0249 1.0000
4.000 0.4591 0.01282 0.00649 -0.0025 0.0221 1.0000
4.250 0.4834 0.01412 0.00791 -0.0015 0.0204 1.0000
4.500 0.5079 0.01561 0.00954 -0.0006 0.0184 1.0000
4.750 0.5320 0.01730 0.01137 0.0002 0.0172 1.0000
5.000 0.5531 0.02115 0.01549 0.0012 0.0156 1.0000
5.250 0.5740 0.02444 0.01926 0.0025 0.0152 1.0000
5.500 0.5949 0.02745 0.02264 0.0037 0.0152 1.0000
5.750 0.6140 0.03095 0.02654 0.0050 0.0151 1.0000
6.000 0.6316 0.03453 0.03049 0.0062 0.0151 1.0000
6.250 0.6483 0.03808 0.03436 0.0073 0.0150 1.0000
6.500 0.6645 0.04153 0.03812 0.0082 0.0148 1.0000
6.750 0.6853 0.04451 0.04141 0.0093 0.0135 1.0000
7.000 0.6981 0.04873 0.04587 0.0096 0.0125 1.0000
7.250 0.7072 0.05323 0.05058 0.0095 0.0120 1.0000
7.500 0.7130 0.05791 0.05543 0.0088 0.0116 1.0000
7.750 0.7153 0.06282 0.06048 0.0076 0.0114 1.0000
8.000 0.7140 0.06790 0.06567 0.0055 0.0112 1.0000
8.250 0.7082 0.07336 0.07121 0.0023 0.0112 1.0000
8.500 0.6952 0.07959 0.07744 -0.0040 0.0114 1.0000
8.750 0.6899 0.08500 0.08282 -0.0082 0.0115 1.0000
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