BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 50,000 Max Cl/Cd: 31.22 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacxxx-il-50000.txt Download as CSV file: xf-bacxxx-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: BOEING BACXXX AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4669 0.11576 0.10878 -0.0072 1.0000 0.3495
-9.250 -0.4373 0.11091 0.10390 -0.0054 1.0000 0.3737
-9.000 -0.4417 0.10883 0.10190 -0.0040 1.0000 0.3944
-8.750 -0.4227 0.10512 0.09819 -0.0026 1.0000 0.4180
-8.500 -0.4205 0.10247 0.09561 -0.0011 1.0000 0.4388
-8.250 -0.4054 0.09888 0.09204 -0.0001 1.0000 0.4580
-8.000 -0.4068 0.09674 0.08996 0.0017 1.0000 0.4781
-7.750 -0.3951 0.09296 0.08622 0.0021 1.0000 0.4892
-6.750 -0.5005 0.07930 0.07321 0.0005 1.0000 0.3944
-6.000 -0.6190 0.05415 0.04716 -0.0194 1.0000 0.2185
-5.750 -0.6016 0.04903 0.04122 -0.0198 1.0000 0.1729
-5.500 -0.5814 0.04558 0.03697 -0.0184 1.0000 0.1450
-5.250 -0.5601 0.04256 0.03335 -0.0169 1.0000 0.1290
-5.000 -0.5376 0.04026 0.03036 -0.0150 1.0000 0.1170
-4.750 -0.5145 0.03748 0.02725 -0.0137 1.0000 0.1102
-4.500 -0.4903 0.03641 0.02541 -0.0117 1.0000 0.1050
-4.250 -0.4659 0.03434 0.02304 -0.0105 1.0000 0.1049
-4.000 -0.4400 0.03217 0.02072 -0.0096 1.0000 0.1056
-3.750 -0.4126 0.03038 0.01880 -0.0086 1.0000 0.1060
-3.500 -0.3844 0.02874 0.01715 -0.0076 1.0000 0.1071
-3.250 -0.3579 0.02738 0.01583 -0.0062 1.0000 0.1104
-3.000 -0.3340 0.02636 0.01470 -0.0047 1.0000 0.1182
-2.750 -0.3119 0.02506 0.01342 -0.0036 1.0000 0.1318
-2.500 -0.0654 0.02550 0.01619 -0.0201 1.0000 0.9903
-2.250 -0.0270 0.02479 0.01518 -0.0243 1.0000 1.0000
-2.000 -0.0250 0.02430 0.01463 -0.0216 1.0000 1.0000
-1.750 -0.0246 0.02382 0.01409 -0.0187 1.0000 1.0000
-1.500 -0.0261 0.02334 0.01356 -0.0155 1.0000 1.0000
-1.250 -0.0300 0.02283 0.01302 -0.0120 1.0000 1.0000
-1.000 -0.0365 0.02230 0.01246 -0.0080 1.0000 1.0000
-0.750 -0.0456 0.02174 0.01188 -0.0036 1.0000 1.0000
-0.500 -0.0539 0.02122 0.01131 0.0008 1.0000 1.0000
-0.250 -0.0544 0.02090 0.01087 0.0041 1.0000 1.0000
0.000 -0.0448 0.02082 0.01065 0.0059 1.0000 1.0000
0.250 -0.0299 0.02091 0.01059 0.0070 1.0000 1.0000
0.500 -0.0126 0.02110 0.01066 0.0076 1.0000 1.0000
0.750 0.0056 0.02137 0.01083 0.0081 1.0000 1.0000
1.000 0.0243 0.02172 0.01107 0.0085 1.0000 1.0000
1.250 0.0430 0.02214 0.01143 0.0088 1.0000 1.0000
1.500 0.0613 0.02264 0.01190 0.0090 1.0000 1.0000
1.750 0.0790 0.02325 0.01248 0.0091 1.0000 1.0000
2.000 0.0957 0.02398 0.01321 0.0091 1.0000 1.0000
2.250 0.1312 0.02516 0.01443 0.0052 0.9916 1.0000
2.500 0.2145 0.02663 0.01601 -0.0070 0.9573 1.0000
2.750 0.2932 0.02734 0.01687 -0.0171 0.9216 1.0000
3.000 0.3647 0.02720 0.01696 -0.0247 0.8825 1.0000
3.250 0.4322 0.02636 0.01635 -0.0303 0.8416 1.0000
3.500 0.5002 0.02485 0.01512 -0.0348 0.8002 1.0000
3.750 0.5623 0.02316 0.01360 -0.0375 0.7552 1.0000
4.000 0.6160 0.02197 0.01239 -0.0391 0.7021 1.0000
4.250 0.6580 0.02174 0.01198 -0.0395 0.6478 1.0000
4.500 0.6875 0.02220 0.01220 -0.0386 0.5996 1.0000
4.750 0.7149 0.02290 0.01266 -0.0378 0.5580 1.0000
5.000 0.7399 0.02379 0.01343 -0.0368 0.5223 1.0000
5.250 0.7644 0.02478 0.01432 -0.0359 0.4919 1.0000
5.500 0.7876 0.02588 0.01540 -0.0349 0.4654 1.0000
5.750 0.8110 0.02701 0.01650 -0.0340 0.4410 1.0000
6.000 0.8331 0.02818 0.01772 -0.0328 0.4179 1.0000
6.250 0.8553 0.02951 0.01910 -0.0318 0.3978 1.0000
6.500 0.8751 0.03086 0.02058 -0.0304 0.3775 1.0000
6.750 0.8978 0.03206 0.02171 -0.0293 0.3568 1.0000
7.000 0.9137 0.03340 0.02325 -0.0274 0.3363 1.0000
7.250 0.9324 0.03471 0.02468 -0.0258 0.3170 1.0000
7.500 0.9518 0.03625 0.02634 -0.0244 0.3003 1.0000
7.750 0.9720 0.03782 0.02796 -0.0231 0.2836 1.0000
8.000 0.9856 0.03954 0.02991 -0.0210 0.2665 1.0000
8.250 0.9987 0.04141 0.03202 -0.0189 0.2504 1.0000
8.500 1.0115 0.04330 0.03414 -0.0168 0.2351 1.0000
8.750 1.0250 0.04542 0.03645 -0.0148 0.2220 1.0000
9.000 1.0434 0.04763 0.03872 -0.0135 0.2107 1.0000
9.250 1.0351 0.05134 0.04306 -0.0098 0.2035 1.0000
9.500 1.0444 0.05377 0.04565 -0.0078 0.1934 1.0000
9.750 1.0397 0.05732 0.04956 -0.0050 0.1872 1.0000
10.000 1.0479 0.06069 0.05306 -0.0034 0.1815 1.0000
10.250 1.0237 0.06593 0.05867 -0.0003 0.1808 1.0000
10.500 0.9961 0.07143 0.06440 0.0021 0.1810 1.0000
10.750 0.9667 0.07698 0.07006 0.0039 0.1818 1.0000
11.000 0.9402 0.08323 0.07635 0.0040 0.1827 1.0000
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Polar data table (+)
Polar graphs
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