BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING VERTOL V13006-.7 AIRFOIL (v13006-il) Reynolds number: 500,000 Max Cl/Cd: 54.73 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-v13006-il-500000.txt Download as CSV file: xf-v13006-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6439 0.09463 0.09240 0.0196 1.0000 0.0163
-8.250 -0.6424 0.09035 0.08813 0.0166 1.0000 0.0167
-8.000 -0.6419 0.08569 0.08350 0.0124 1.0000 0.0172
-7.750 -0.6375 0.07991 0.07771 0.0051 1.0000 0.0177
-7.500 -0.6253 0.07314 0.07086 -0.0034 1.0000 0.0183
-7.250 -0.6115 0.06755 0.06513 -0.0082 1.0000 0.0186
-7.000 -0.5983 0.06263 0.06008 -0.0108 1.0000 0.0187
-6.750 -0.5845 0.05788 0.05516 -0.0126 1.0000 0.0187
-6.500 -0.5700 0.05329 0.05036 -0.0137 1.0000 0.0188
-6.250 -0.5664 0.04566 0.04257 -0.0152 1.0000 0.0195
-6.000 -0.5500 0.04279 0.03960 -0.0154 1.0000 0.0199
-5.750 -0.5317 0.04014 0.03683 -0.0156 1.0000 0.0205
-5.500 -0.5117 0.03732 0.03385 -0.0156 1.0000 0.0215
-5.250 -0.4900 0.03434 0.03066 -0.0153 1.0000 0.0231
-5.000 -0.4603 0.03372 0.02964 -0.0140 1.0000 0.0256
-4.750 -0.4451 0.02720 0.02261 -0.0134 1.0000 0.0267
-4.500 -0.4236 0.02484 0.02019 -0.0131 1.0000 0.0278
-4.250 -0.4005 0.02335 0.01861 -0.0127 1.0000 0.0293
-4.000 -0.3762 0.02203 0.01712 -0.0121 1.0000 0.0321
-3.750 -0.3481 0.02303 0.01791 -0.0109 1.0000 0.0353
-3.500 -0.3278 0.01833 0.01281 -0.0101 1.0000 0.0377
-3.250 -0.3006 0.01398 0.00799 -0.0080 1.0000 0.0221
-3.000 -0.2755 0.01262 0.00647 -0.0070 1.0000 0.0220
-2.750 -0.2507 0.01169 0.00547 -0.0062 1.0000 0.0225
-2.500 -0.2260 0.01101 0.00476 -0.0054 1.0000 0.0235
-2.250 -0.2011 0.01058 0.00431 -0.0047 1.0000 0.0250
-2.000 -0.1764 0.01006 0.00376 -0.0039 1.0000 0.0256
-1.750 -0.1523 0.00909 0.00275 -0.0031 1.0000 0.0277
-1.500 -0.1273 0.00869 0.00236 -0.0025 1.0000 0.0309
-1.250 -0.1021 0.00846 0.00213 -0.0020 1.0000 0.0352
-1.000 -0.0676 0.00797 0.00167 -0.0034 0.9969 0.0541
-0.750 -0.0354 0.00566 0.00143 -0.0057 0.9921 0.6337
-0.500 -0.0071 0.00477 0.00158 -0.0047 0.9853 0.9355
-0.250 0.0564 0.00478 0.00156 -0.0121 0.9843 1.0000
0.000 0.0954 0.00475 0.00148 -0.0144 0.9661 1.0000
0.250 0.1305 0.00472 0.00140 -0.0158 0.9399 1.0000
0.500 0.1580 0.00472 0.00132 -0.0154 0.9037 1.0000
0.750 0.1821 0.00479 0.00124 -0.0141 0.8593 1.0000
1.000 0.2061 0.00493 0.00119 -0.0130 0.8083 1.0000
1.250 0.2303 0.00514 0.00116 -0.0119 0.7522 1.0000
1.500 0.2547 0.00540 0.00117 -0.0110 0.6884 1.0000
1.750 0.2793 0.00570 0.00119 -0.0103 0.6228 1.0000
2.000 0.3038 0.00608 0.00124 -0.0096 0.5421 1.0000
2.250 0.3280 0.00655 0.00131 -0.0090 0.4455 1.0000
2.500 0.3531 0.00695 0.00142 -0.0086 0.3732 1.0000
2.750 0.3786 0.00731 0.00154 -0.0082 0.3162 1.0000
3.000 0.4041 0.00769 0.00168 -0.0079 0.2630 1.0000
3.250 0.4301 0.00797 0.00183 -0.0076 0.2256 1.0000
3.500 0.4559 0.00833 0.00201 -0.0073 0.1804 1.0000
3.750 0.4802 0.00910 0.00233 -0.0070 0.0811 1.0000
4.000 0.5048 0.01001 0.00299 -0.0064 0.0275 1.0000
4.250 0.5310 0.01045 0.00350 -0.0060 0.0247 1.0000
4.500 0.5571 0.01087 0.00398 -0.0056 0.0231 1.0000
4.750 0.5831 0.01129 0.00443 -0.0053 0.0215 1.0000
5.000 0.6087 0.01185 0.00503 -0.0049 0.0205 1.0000
5.250 0.6335 0.01263 0.00586 -0.0044 0.0198 1.0000
5.500 0.6571 0.01379 0.00712 -0.0037 0.0191 1.0000
5.750 0.6804 0.01516 0.00856 -0.0029 0.0188 1.0000
6.000 0.7050 0.01624 0.00972 -0.0023 0.0187 1.0000
6.250 0.7291 0.01769 0.01129 -0.0016 0.0186 1.0000
6.500 0.7522 0.02007 0.01382 -0.0008 0.0189 1.0000
6.750 0.7765 0.02152 0.01542 -0.0003 0.0190 1.0000
7.000 0.7991 0.02368 0.01781 0.0004 0.0190 1.0000
7.250 0.8236 0.02464 0.01893 0.0010 0.0193 1.0000
7.500 0.7992 0.01964 0.01564 0.0075 0.0310 1.0000
7.750 0.8129 0.02266 0.01893 0.0084 0.0297 1.0000
8.000 0.8253 0.02576 0.02222 0.0092 0.0287 1.0000
8.250 0.8366 0.02895 0.02558 0.0099 0.0280 1.0000
8.500 0.8479 0.03241 0.02908 0.0104 0.0273 1.0000
8.750 0.8407 0.03981 0.03668 0.0108 0.0264 1.0000
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Polar data table (+)
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