BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING-VERTOL VR-9 AIRFOIL (vr9-il) Reynolds number: 100,000 Max Cl/Cd: 31.2 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-vr9-il-100000.txt Download as CSV file: xf-vr9-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6493 0.09257 0.08794 0.0047 1.0000 0.0905
-8.000 -0.6627 0.08807 0.08347 -0.0031 1.0000 0.0916
-7.750 -0.6745 0.08444 0.07965 -0.0096 1.0000 0.0923
-7.500 -0.6484 0.07941 0.07486 -0.0020 1.0000 0.1004
-7.250 -0.6584 0.07506 0.07026 -0.0105 1.0000 0.1054
-7.000 -0.6462 0.06976 0.06509 -0.0088 1.0000 0.1094
-6.750 -0.6486 0.06751 0.06227 -0.0140 1.0000 0.1195
-6.500 -0.6298 0.06149 0.05667 -0.0113 1.0000 0.1243
-6.250 -0.6205 0.05745 0.05247 -0.0126 1.0000 0.1363
-6.000 -0.6082 0.05389 0.04876 -0.0128 1.0000 0.1504
-5.750 -0.5971 0.05081 0.04546 -0.0133 1.0000 0.1749
-5.500 -0.5836 0.04780 0.04248 -0.0122 1.0000 0.2025
-4.500 -0.4691 0.02828 0.01999 -0.0119 1.0000 0.0733
-4.250 -0.4407 0.02547 0.01650 -0.0103 1.0000 0.0631
-4.000 -0.4143 0.02281 0.01352 -0.0092 1.0000 0.0604
-3.750 -0.3876 0.02090 0.01133 -0.0081 1.0000 0.0618
-3.500 -0.3612 0.01940 0.00960 -0.0071 1.0000 0.0662
-3.250 -0.3365 0.01756 0.00775 -0.0061 1.0000 0.0686
-3.000 -0.3131 0.01630 0.00655 -0.0049 1.0000 0.0729
-2.750 -0.2904 0.01530 0.00555 -0.0038 1.0000 0.0837
-2.500 -0.2670 0.01444 0.00460 -0.0027 1.0000 0.0936
-2.250 -0.2466 0.01267 0.00361 -0.0015 1.0000 0.2279
-2.000 -0.2398 0.01032 0.00372 0.0046 1.0000 0.8154
-1.750 -0.1523 0.01034 0.00342 -0.0051 1.0000 0.9778
-1.500 -0.1013 0.01021 0.00300 -0.0103 1.0000 1.0000
-1.250 -0.0828 0.01008 0.00274 -0.0090 1.0000 1.0000
-1.000 -0.0636 0.00999 0.00254 -0.0077 1.0000 1.0000
-0.750 -0.0441 0.00993 0.00241 -0.0064 1.0000 1.0000
-0.500 -0.0247 0.00990 0.00229 -0.0051 1.0000 1.0000
-0.250 -0.0054 0.00990 0.00224 -0.0038 1.0000 1.0000
0.000 0.0139 0.00992 0.00225 -0.0024 1.0000 1.0000
0.250 0.0332 0.00996 0.00230 -0.0011 1.0000 1.0000
0.500 0.0521 0.01004 0.00240 0.0002 1.0000 1.0000
0.750 0.0703 0.01017 0.00256 0.0015 1.0000 1.0000
1.000 0.0872 0.01035 0.00281 0.0029 1.0000 1.0000
1.250 0.1039 0.01060 0.00311 0.0041 0.9995 1.0000
1.500 0.1792 0.01067 0.00340 -0.0057 0.9698 1.0000
1.750 0.2423 0.01057 0.00352 -0.0123 0.9306 1.0000
2.000 0.2867 0.01055 0.00374 -0.0150 0.8895 1.0000
2.250 0.3187 0.01062 0.00392 -0.0148 0.8400 1.0000
2.500 0.3382 0.01084 0.00391 -0.0110 0.7379 1.0000
2.750 0.3520 0.01159 0.00388 -0.0064 0.5276 1.0000
3.000 0.3631 0.01456 0.00464 -0.0039 0.1007 1.0000
3.250 0.3860 0.01561 0.00566 -0.0029 0.0800 1.0000
3.500 0.4095 0.01650 0.00668 -0.0018 0.0735 1.0000
3.750 0.4322 0.01771 0.00787 -0.0006 0.0695 1.0000
4.000 0.4557 0.01961 0.00965 0.0006 0.0672 1.0000
4.250 0.4819 0.02080 0.01107 0.0015 0.0613 1.0000
4.500 0.5087 0.02286 0.01334 0.0026 0.0605 1.0000
4.750 0.5357 0.02548 0.01633 0.0037 0.0626 1.0000
5.000 0.5613 0.02867 0.01995 0.0048 0.0653 1.0000
5.250 0.5854 0.03154 0.02330 0.0060 0.0650 1.0000
5.500 0.6101 0.03701 0.02920 0.0071 0.0797 1.0000
6.750 0.6974 0.06225 0.05749 0.0043 0.1531 1.0000
7.000 0.7027 0.06647 0.06180 0.0033 0.1412 1.0000
7.750 0.6337 0.07224 0.06802 -0.0018 0.1315 1.0000
8.000 0.6117 0.07739 0.07309 -0.0067 0.1287 1.0000
8.250 0.6427 0.08173 0.07746 -0.0005 0.1199 1.0000
8.500 0.6162 0.08683 0.08248 -0.0069 0.1192 1.0000
8.750 0.5965 0.09153 0.08710 -0.0118 0.1160 1.0000
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Polar data table (+)
Polar graphs
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