BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 500,000 Max Cl/Cd: 53.74 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-v13006-il-500000-n5.txt Download as CSV file: xf-v13006-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING VERTOL V13006-.7 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6487 0.09740 0.09514 0.0216 1.0000 0.0114
-8.500 -0.6479 0.09298 0.09073 0.0189 1.0000 0.0114
-8.000 -0.6539 0.07902 0.07680 0.0054 1.0000 0.0095
-7.750 -0.6484 0.07381 0.07155 0.0005 1.0000 0.0094
-7.500 -0.6410 0.06825 0.06592 -0.0041 1.0000 0.0092
-7.250 -0.6318 0.06246 0.06003 -0.0080 1.0000 0.0091
-7.000 -0.6206 0.05657 0.05399 -0.0111 1.0000 0.0090
-6.750 -0.6075 0.05060 0.04782 -0.0133 1.0000 0.0090
-6.500 -0.5926 0.04472 0.04168 -0.0146 1.0000 0.0091
-6.250 -0.5759 0.03913 0.03580 -0.0149 1.0000 0.0093
-6.000 -0.5579 0.03394 0.03025 -0.0147 1.0000 0.0094
-5.750 -0.5380 0.02848 0.02434 -0.0138 1.0000 0.0098
-5.250 -0.4966 0.02096 0.01592 -0.0120 1.0000 0.0098
-5.000 -0.4740 0.01810 0.01263 -0.0111 1.0000 0.0099
-4.750 -0.4508 0.01568 0.00984 -0.0103 1.0000 0.0102
-4.500 -0.4261 0.01447 0.00847 -0.0098 1.0000 0.0105
-4.250 -0.4009 0.01364 0.00754 -0.0092 1.0000 0.0109
-4.000 -0.3758 0.01290 0.00671 -0.0087 1.0000 0.0113
-3.750 -0.3507 0.01221 0.00594 -0.0081 1.0000 0.0118
-3.500 -0.3258 0.01154 0.00521 -0.0074 1.0000 0.0123
-3.250 -0.3010 0.01096 0.00455 -0.0067 1.0000 0.0129
-3.000 -0.2760 0.01060 0.00416 -0.0061 1.0000 0.0136
-2.750 -0.2515 0.01002 0.00355 -0.0054 1.0000 0.0144
-2.500 -0.2249 0.00950 0.00302 -0.0052 0.9990 0.0153
-2.250 -0.1886 0.00913 0.00263 -0.0071 0.9920 0.0164
-2.000 -0.1532 0.00881 0.00230 -0.0087 0.9820 0.0179
-1.750 -0.1179 0.00855 0.00202 -0.0103 0.9681 0.0195
-1.500 -0.0840 0.00826 0.00174 -0.0115 0.9479 0.0246
-1.250 -0.0528 0.00808 0.00151 -0.0120 0.9200 0.0312
-1.000 -0.0261 0.00795 0.00134 -0.0114 0.8826 0.0429
-0.750 -0.0016 0.00776 0.00120 -0.0105 0.8361 0.1002
-0.500 0.0192 0.00650 0.00101 -0.0097 0.7919 0.4750
-0.250 0.0368 0.00553 0.00099 -0.0075 0.7466 0.7750
0.000 0.0561 0.00534 0.00105 -0.0048 0.7009 0.9109
0.250 0.0906 0.00551 0.00106 -0.0059 0.6518 0.9654
0.500 0.1328 0.00573 0.00106 -0.0089 0.6004 0.9909
0.750 0.1708 0.00595 0.00105 -0.0112 0.5484 1.0000
1.000 0.1962 0.00623 0.00105 -0.0108 0.4846 1.0000
1.250 0.2216 0.00654 0.00108 -0.0104 0.4181 1.0000
1.500 0.2467 0.00692 0.00112 -0.0100 0.3408 1.0000
1.750 0.2719 0.00726 0.00119 -0.0097 0.2798 1.0000
2.000 0.2974 0.00757 0.00127 -0.0093 0.2292 1.0000
2.250 0.3230 0.00787 0.00137 -0.0090 0.1839 1.0000
2.500 0.3490 0.00807 0.00148 -0.0086 0.1627 1.0000
2.750 0.3751 0.00829 0.00161 -0.0083 0.1419 1.0000
3.000 0.4002 0.00882 0.00182 -0.0080 0.0728 1.0000
3.250 0.4257 0.00928 0.00211 -0.0076 0.0315 1.0000
3.500 0.4520 0.00953 0.00234 -0.0073 0.0208 1.0000
3.750 0.4784 0.00980 0.00258 -0.0070 0.0174 1.0000
4.000 0.5048 0.01006 0.00284 -0.0067 0.0159 1.0000
4.250 0.5312 0.01037 0.00318 -0.0064 0.0146 1.0000
4.500 0.5575 0.01067 0.00352 -0.0061 0.0140 1.0000
4.750 0.5838 0.01101 0.00390 -0.0058 0.0136 1.0000
5.000 0.6099 0.01139 0.00433 -0.0055 0.0132 1.0000
5.250 0.6358 0.01183 0.00484 -0.0052 0.0128 1.0000
5.500 0.6615 0.01231 0.00538 -0.0049 0.0124 1.0000
5.750 0.6870 0.01286 0.00598 -0.0045 0.0121 1.0000
6.000 0.7121 0.01348 0.00666 -0.0041 0.0118 1.0000
6.250 0.7367 0.01421 0.00747 -0.0037 0.0115 1.0000
6.500 0.7609 0.01506 0.00839 -0.0032 0.0112 1.0000
6.750 0.7844 0.01610 0.00953 -0.0026 0.0110 1.0000
7.000 0.8066 0.01757 0.01113 -0.0019 0.0106 1.0000
7.250 0.8313 0.01825 0.01194 -0.0015 0.0104 1.0000
7.500 0.8549 0.01926 0.01310 -0.0010 0.0102 1.0000
7.750 0.8780 0.02042 0.01443 -0.0004 0.0101 1.0000
8.000 0.9004 0.02175 0.01595 0.0002 0.0099 1.0000
8.250 0.9220 0.02326 0.01769 0.0009 0.0097 1.0000
8.500 0.9424 0.02500 0.01969 0.0016 0.0095 1.0000
8.750 0.9612 0.02705 0.02204 0.0024 0.0093 1.0000
9.000 0.9777 0.02946 0.02478 0.0032 0.0091 1.0000
9.250 0.9914 0.03233 0.02801 0.0041 0.0089 1.0000
9.500 1.0011 0.03572 0.03178 0.0051 0.0087 1.0000
9.750 1.0088 0.03897 0.03534 0.0058 0.0085 1.0000
10.000 1.0150 0.04198 0.03860 0.0063 0.0084 1.0000
10.250 1.0187 0.04490 0.04175 0.0067 0.0082 1.0000
10.500 1.0178 0.04807 0.04511 0.0067 0.0081 1.0000
10.750 1.0018 0.05245 0.04971 0.0062 0.0081 1.0000
11.000 0.8589 0.09875 0.09651 -0.0290 0.0092 1.0000
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Polar data table (+)
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