BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 1,000,000 Max Cl/Cd: 62.36 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13006-il-1000000.txt Download as CSV file: xf-v13006-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6543 0.09401 0.09242 0.0184 1.0000 0.0100
-8.500 -0.6659 0.08712 0.08556 0.0142 1.0000 0.0102
-8.250 -0.6664 0.08228 0.08073 0.0093 1.0000 0.0103
-8.000 -0.6612 0.07689 0.07532 0.0033 1.0000 0.0104
-7.750 -0.6535 0.07196 0.07034 -0.0012 1.0000 0.0105
-7.500 -0.6440 0.06727 0.06561 -0.0048 1.0000 0.0106
-7.250 -0.6328 0.06272 0.06098 -0.0078 1.0000 0.0107
-7.000 -0.6197 0.05840 0.05657 -0.0103 1.0000 0.0109
-6.750 -0.6049 0.05422 0.05228 -0.0122 1.0000 0.0113
-6.500 -0.5887 0.04993 0.04786 -0.0137 1.0000 0.0117
-6.250 -0.5709 0.04541 0.04318 -0.0148 1.0000 0.0123
-6.000 -0.5460 0.04067 0.03818 -0.0148 1.0000 0.0135
-5.750 -0.5254 0.03656 0.03381 -0.0146 1.0000 0.0137
-5.500 -0.5060 0.03237 0.02933 -0.0140 1.0000 0.0137
-4.250 -0.4009 0.01545 0.01071 -0.0096 1.0000 0.0140
-4.000 -0.3764 0.01405 0.00914 -0.0088 1.0000 0.0140
-3.750 -0.3519 0.01263 0.00761 -0.0080 1.0000 0.0135
-3.500 -0.3276 0.01129 0.00612 -0.0070 1.0000 0.0136
-3.250 -0.3036 0.01006 0.00477 -0.0061 1.0000 0.0140
-3.000 -0.2799 0.00904 0.00371 -0.0053 1.0000 0.0148
-2.750 -0.2552 0.00862 0.00328 -0.0046 1.0000 0.0154
-2.500 -0.2305 0.00826 0.00291 -0.0039 1.0000 0.0161
-2.000 -0.1603 0.00762 0.00225 -0.0071 0.9944 0.0183
-1.750 -0.1250 0.00713 0.00171 -0.0087 0.9888 0.0207
-1.500 -0.0898 0.00689 0.00150 -0.0102 0.9808 0.0239
-1.250 -0.0558 0.00663 0.00124 -0.0114 0.9683 0.0312
-1.000 -0.0254 0.00641 0.00106 -0.0118 0.9466 0.0514
-0.750 -0.0005 0.00570 0.00091 -0.0113 0.9190 0.2426
-0.500 0.0211 0.00469 0.00078 -0.0104 0.8879 0.5483
-0.250 0.0419 0.00401 0.00074 -0.0088 0.8532 0.7695
0.000 0.0591 0.00367 0.00079 -0.0057 0.8143 0.9263
0.250 0.0937 0.00383 0.00083 -0.0067 0.7661 0.9846
0.500 0.1334 0.00410 0.00082 -0.0092 0.6984 0.9952
0.750 0.1712 0.00438 0.00081 -0.0115 0.6276 1.0000
1.000 0.1974 0.00458 0.00081 -0.0112 0.5757 1.0000
1.250 0.2235 0.00479 0.00082 -0.0108 0.5221 1.0000
1.500 0.2490 0.00513 0.00085 -0.0105 0.4405 1.0000
1.750 0.2746 0.00545 0.00090 -0.0101 0.3717 1.0000
2.000 0.3001 0.00580 0.00097 -0.0098 0.3035 1.0000
2.250 0.3258 0.00606 0.00105 -0.0094 0.2610 1.0000
2.500 0.3518 0.00625 0.00114 -0.0091 0.2311 1.0000
2.750 0.3775 0.00654 0.00123 -0.0087 0.1878 1.0000
3.000 0.4035 0.00678 0.00136 -0.0084 0.1585 1.0000
3.250 0.4291 0.00719 0.00152 -0.0081 0.1024 1.0000
3.500 0.4538 0.00791 0.00191 -0.0077 0.0258 1.0000
3.750 0.4802 0.00818 0.00215 -0.0073 0.0183 1.0000
4.000 0.5068 0.00842 0.00240 -0.0070 0.0168 1.0000
4.250 0.5334 0.00869 0.00267 -0.0067 0.0157 1.0000
4.500 0.5599 0.00901 0.00303 -0.0064 0.0150 1.0000
4.750 0.5862 0.00940 0.00346 -0.0061 0.0145 1.0000
5.000 0.6122 0.00991 0.00405 -0.0057 0.0141 1.0000
5.250 0.6374 0.01062 0.00486 -0.0052 0.0136 1.0000
5.500 0.6633 0.01109 0.00538 -0.0049 0.0134 1.0000
5.750 0.6889 0.01167 0.00603 -0.0045 0.0132 1.0000
6.000 0.7138 0.01242 0.00685 -0.0040 0.0129 1.0000
6.250 0.7383 0.01335 0.00786 -0.0034 0.0128 1.0000
6.500 0.7630 0.01420 0.00880 -0.0029 0.0126 1.0000
6.750 0.7874 0.01521 0.00990 -0.0024 0.0124 1.0000
7.000 0.8111 0.01656 0.01138 -0.0017 0.0124 1.0000
7.250 0.8343 0.01813 0.01312 -0.0010 0.0125 1.0000
7.500 0.8566 0.02005 0.01526 -0.0002 0.0126 1.0000
7.750 0.8771 0.02256 0.01804 0.0007 0.0128 1.0000
8.750 0.9154 0.04203 0.03905 0.0049 0.0137 1.0000
9.000 0.9199 0.04597 0.04329 0.0055 0.0137 1.0000
9.250 0.9200 0.05010 0.04771 0.0058 0.0136 1.0000
13.500 0.6214 0.14419 0.14261 -0.0318 0.0124 1.0000
13.750 0.6182 0.14713 0.14556 -0.0328 0.0118 1.0000
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Polar data table (+)
Polar graphs
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