BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 50,000 Max Cl/Cd: 30.76 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacxxx-il-50000-n5.txt Download as CSV file: xf-bacxxx-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4015 0.09554 0.08882 -0.0380 1.0000 0.0594
-9.750 -0.4045 0.09124 0.08456 -0.0384 1.0000 0.0568
-9.500 -0.4141 0.08603 0.07940 -0.0400 1.0000 0.0545
-9.250 -0.4327 0.07985 0.07326 -0.0430 1.0000 0.0524
-9.000 -0.4617 0.07415 0.06756 -0.0456 1.0000 0.0510
-8.750 -0.4954 0.07026 0.06364 -0.0454 1.0000 0.0502
-8.500 -0.5303 0.06787 0.06118 -0.0422 1.0000 0.0494
-8.250 -0.5339 0.06451 0.05776 -0.0403 1.0000 0.0476
-8.000 -0.6053 0.07125 0.06388 -0.0368 1.0000 0.0475
-7.750 -0.6066 0.06777 0.06031 -0.0350 1.0000 0.0465
-7.500 -0.6087 0.06449 0.05689 -0.0329 1.0000 0.0456
-7.250 -0.6094 0.06126 0.05349 -0.0308 1.0000 0.0446
-7.000 -0.6080 0.05809 0.05009 -0.0285 1.0000 0.0436
-6.750 -0.6043 0.05496 0.04668 -0.0263 1.0000 0.0427
-6.500 -0.5979 0.05192 0.04331 -0.0241 1.0000 0.0417
-6.250 -0.5890 0.04899 0.04000 -0.0219 1.0000 0.0409
-6.000 -0.5771 0.04620 0.03683 -0.0198 1.0000 0.0402
-5.750 -0.5629 0.04358 0.03381 -0.0178 1.0000 0.0397
-5.500 -0.5463 0.04114 0.03098 -0.0160 1.0000 0.0393
-5.250 -0.5277 0.03888 0.02835 -0.0144 1.0000 0.0392
-5.000 -0.5074 0.03680 0.02595 -0.0130 1.0000 0.0394
-4.750 -0.4863 0.03498 0.02385 -0.0117 1.0000 0.0405
-4.500 -0.4642 0.03340 0.02206 -0.0106 1.0000 0.0427
-4.250 -0.4408 0.03196 0.02039 -0.0094 1.0000 0.0450
-4.000 -0.4164 0.03063 0.01887 -0.0081 1.0000 0.0467
-3.750 -0.3922 0.02944 0.01753 -0.0067 1.0000 0.0479
-3.500 -0.3699 0.02821 0.01621 -0.0052 1.0000 0.0496
-3.250 -0.3498 0.02707 0.01504 -0.0038 1.0000 0.0530
-3.000 -0.3292 0.02622 0.01403 -0.0026 1.0000 0.0595
-2.750 -0.3080 0.02521 0.01291 -0.0018 1.0000 0.0668
-2.500 -0.2858 0.02425 0.01184 -0.0011 1.0000 0.0806
-2.250 -0.2624 0.02280 0.01064 -0.0010 1.0000 0.1265
-2.000 -0.2576 0.02028 0.01094 0.0044 1.0000 0.6894
-1.750 -0.2523 0.02036 0.01143 0.0119 1.0000 0.8053
-1.500 -0.2308 0.02084 0.01198 0.0169 1.0000 0.8972
-1.250 -0.1952 0.02088 0.01173 0.0150 1.0000 0.9217
-1.000 -0.1544 0.02094 0.01150 0.0117 1.0000 0.9427
-0.750 -0.1117 0.02101 0.01134 0.0077 1.0000 0.9662
-0.500 -0.0675 0.02109 0.01121 0.0032 1.0000 0.9921
-0.250 -0.0544 0.02090 0.01087 0.0041 1.0000 1.0000
0.000 -0.0379 0.02089 0.01071 0.0046 0.9978 1.0000
0.250 0.0142 0.02130 0.01092 -0.0013 0.9846 1.0000
0.500 0.0617 0.02158 0.01105 -0.0061 0.9706 1.0000
0.750 0.1062 0.02180 0.01116 -0.0102 0.9568 1.0000
1.000 0.1501 0.02194 0.01124 -0.0139 0.9419 1.0000
1.250 0.1935 0.02199 0.01125 -0.0173 0.9261 1.0000
1.500 0.2365 0.02197 0.01122 -0.0205 0.9098 1.0000
1.750 0.2726 0.02186 0.01113 -0.0221 0.8907 1.0000
2.000 0.3099 0.02168 0.01099 -0.0238 0.8709 1.0000
2.250 0.3482 0.02141 0.01078 -0.0254 0.8502 1.0000
2.500 0.3816 0.02109 0.01054 -0.0259 0.8255 1.0000
2.750 0.4124 0.02076 0.01028 -0.0257 0.7965 1.0000
3.000 0.4414 0.02047 0.01004 -0.0252 0.7606 1.0000
3.250 0.4784 0.02008 0.00966 -0.0259 0.7188 1.0000
3.500 0.5203 0.01974 0.00925 -0.0272 0.6660 1.0000
3.750 0.5569 0.01974 0.00899 -0.0278 0.6064 1.0000
4.000 0.5856 0.02010 0.00903 -0.0274 0.5547 1.0000
4.250 0.6098 0.02064 0.00936 -0.0265 0.5132 1.0000
4.500 0.6325 0.02124 0.00977 -0.0255 0.4787 1.0000
4.750 0.6547 0.02186 0.01025 -0.0245 0.4481 1.0000
5.000 0.6765 0.02248 0.01077 -0.0235 0.4203 1.0000
5.250 0.6986 0.02311 0.01136 -0.0226 0.3951 1.0000
5.500 0.7215 0.02376 0.01195 -0.0218 0.3731 1.0000
5.750 0.7453 0.02443 0.01262 -0.0213 0.3536 1.0000
6.000 0.7697 0.02512 0.01338 -0.0209 0.3353 1.0000
6.250 0.7937 0.02583 0.01419 -0.0204 0.3177 1.0000
6.500 0.8171 0.02656 0.01498 -0.0198 0.3012 1.0000
6.750 0.8408 0.02735 0.01585 -0.0192 0.2860 1.0000
7.000 0.8634 0.02816 0.01674 -0.0185 0.2708 1.0000
7.250 0.8836 0.02891 0.01757 -0.0174 0.2546 1.0000
7.500 0.9024 0.02968 0.01844 -0.0162 0.2379 1.0000
7.750 0.9212 0.03050 0.01940 -0.0150 0.2224 1.0000
8.000 0.9412 0.03144 0.02044 -0.0139 0.2093 1.0000
8.250 0.9604 0.03240 0.02151 -0.0128 0.1966 1.0000
8.500 0.9775 0.03338 0.02267 -0.0114 0.1832 1.0000
8.750 0.9933 0.03442 0.02387 -0.0099 0.1698 1.0000
9.000 1.0086 0.03560 0.02525 -0.0083 0.1572 1.0000
9.250 1.0234 0.03693 0.02678 -0.0068 0.1458 1.0000
9.500 1.0389 0.03842 0.02843 -0.0053 0.1366 1.0000
9.750 1.0527 0.03972 0.02980 -0.0038 0.1278 1.0000
10.000 1.0629 0.04146 0.03186 -0.0018 0.1187 1.0000
10.250 1.0750 0.04316 0.03371 -0.0002 0.1120 1.0000
10.500 1.0837 0.04550 0.03643 0.0017 0.1058 1.0000
10.750 1.0966 0.04718 0.03805 0.0031 0.1003 1.0000
11.000 1.0922 0.04998 0.04140 0.0061 0.0949 1.0000
11.250 1.0932 0.05164 0.04318 0.0086 0.0894 1.0000
11.500 1.0893 0.05414 0.04589 0.0110 0.0852 1.0000
11.750 1.0765 0.05736 0.04947 0.0135 0.0817 1.0000
12.000 1.0724 0.05953 0.05173 0.0152 0.0775 1.0000
12.250 1.0653 0.06244 0.05475 0.0164 0.0744 1.0000
12.500 1.0432 0.06740 0.06004 0.0167 0.0733 1.0000
12.750 1.0185 0.07325 0.06616 0.0155 0.0728 1.0000
13.000 0.9904 0.08046 0.07358 0.0125 0.0731 1.0000
13.250 0.9593 0.08938 0.08264 0.0075 0.0740 1.0000
13.500 0.9268 0.09989 0.09322 0.0013 0.0750 1.0000
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Polar data table (+)
Polar graphs
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