BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 500,000 Max Cl/Cd: 75.18 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacxxx-il-500000.txt Download as CSV file: xf-bacxxx-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4027 0.08382 0.08170 -0.0360 1.0000 0.0167
-9.750 -0.4131 0.07895 0.07686 -0.0369 1.0000 0.0167
-9.500 -0.4265 0.07356 0.07150 -0.0382 1.0000 0.0168
-9.250 -0.4490 0.06642 0.06437 -0.0415 1.0000 0.0164
-9.000 -0.4818 0.06032 0.05823 -0.0437 1.0000 0.0160
-8.750 -0.5190 0.05631 0.05419 -0.0428 1.0000 0.0156
-8.500 -0.5578 0.05418 0.05201 -0.0382 1.0000 0.0154
-8.250 -0.5847 0.05185 0.04961 -0.0338 0.9996 0.0153
-8.000 -0.5813 0.04717 0.04480 -0.0358 0.9966 0.0156
-7.750 -0.5748 0.04266 0.04013 -0.0372 0.9941 0.0161
-7.500 -0.5668 0.03845 0.03573 -0.0377 0.9906 0.0168
-7.250 -0.5518 0.03424 0.03126 -0.0383 0.9880 0.0182
-7.000 -0.5265 0.03246 0.02905 -0.0383 0.9858 0.0194
-6.750 -0.5293 0.02517 0.02138 -0.0369 0.9809 0.0201
-6.500 -0.5099 0.02193 0.01809 -0.0377 0.9789 0.0207
-6.250 -0.4868 0.01943 0.01548 -0.0386 0.9774 0.0216
-6.000 -0.4644 0.01720 0.01307 -0.0388 0.9753 0.0226
-5.750 -0.4461 0.01548 0.01114 -0.0375 0.9710 0.0240
-5.500 -0.4141 0.01595 0.01130 -0.0373 0.9686 0.0266
-5.250 -0.3959 0.01100 0.00595 -0.0372 0.9670 0.0282
-5.000 -0.3668 0.00924 0.00416 -0.0383 0.9660 0.0296
-4.750 -0.3361 0.00795 0.00274 -0.0393 0.9650 0.0318
-4.500 -0.3382 0.01867 0.01265 -0.0339 0.9676 0.0182
-4.250 -0.3065 0.01665 0.01048 -0.0343 0.9668 0.0171
-4.000 -0.2727 0.01541 0.00914 -0.0354 0.9658 0.0170
-3.750 -0.2459 0.01460 0.00829 -0.0352 0.9621 0.0174
-3.500 -0.2142 0.01400 0.00765 -0.0360 0.9581 0.0185
-3.250 -0.1759 0.01305 0.00665 -0.0382 0.9554 0.0187
-3.000 -0.1322 0.01217 0.00570 -0.0415 0.9535 0.0190
-2.750 -0.0872 0.01132 0.00477 -0.0451 0.9520 0.0202
-2.500 -0.0649 0.01085 0.00427 -0.0437 0.9440 0.0236
-2.250 -0.0412 0.00871 0.00342 -0.0439 0.9406 0.3914
-2.000 -0.0116 0.00794 0.00326 -0.0444 0.9383 0.5672
-1.750 0.0100 0.00775 0.00322 -0.0429 0.9315 0.6154
-1.500 0.0394 0.00755 0.00311 -0.0431 0.9276 0.6493
-1.250 0.0709 0.00735 0.00296 -0.0436 0.9244 0.6763
-1.000 0.0958 0.00724 0.00289 -0.0427 0.9179 0.6987
-0.750 0.1249 0.00706 0.00273 -0.0428 0.9124 0.7122
-0.500 0.1535 0.00687 0.00256 -0.0427 0.9055 0.7231
-0.250 0.1816 0.00668 0.00239 -0.0425 0.8967 0.7352
0.000 0.2080 0.00654 0.00226 -0.0419 0.8856 0.7485
0.250 0.2352 0.00640 0.00215 -0.0415 0.8739 0.7630
0.500 0.2624 0.00628 0.00206 -0.0411 0.8607 0.7789
0.750 0.2893 0.00619 0.00199 -0.0407 0.8458 0.7962
1.000 0.3159 0.00611 0.00193 -0.0402 0.8266 0.8148
1.250 0.3417 0.00607 0.00188 -0.0394 0.7995 0.8348
1.500 0.3661 0.00609 0.00184 -0.0384 0.7584 0.8564
1.750 0.3875 0.00629 0.00184 -0.0367 0.6983 0.8801
2.000 0.4059 0.00668 0.00195 -0.0344 0.6175 0.9055
2.250 0.4257 0.00718 0.00213 -0.0326 0.5396 0.9290
2.500 0.4507 0.00760 0.00231 -0.0321 0.4846 0.9494
2.750 0.4807 0.00797 0.00248 -0.0327 0.4390 0.9644
3.000 0.5137 0.00831 0.00266 -0.0340 0.4024 0.9758
3.250 0.5503 0.00864 0.00284 -0.0362 0.3708 0.9830
3.500 0.5882 0.00894 0.00301 -0.0387 0.3445 0.9888
3.750 0.6260 0.00919 0.00318 -0.0412 0.3231 0.9944
4.250 0.6923 0.00963 0.00349 -0.0442 0.2877 1.0000
4.500 0.7124 0.00981 0.00363 -0.0428 0.2744 1.0000
4.750 0.7329 0.01001 0.00380 -0.0415 0.2617 1.0000
5.000 0.7536 0.01022 0.00396 -0.0402 0.2475 1.0000
5.250 0.7744 0.01046 0.00413 -0.0390 0.2308 1.0000
5.500 0.7956 0.01070 0.00431 -0.0378 0.2156 1.0000
5.750 0.8170 0.01093 0.00452 -0.0367 0.2027 1.0000
6.000 0.8386 0.01119 0.00474 -0.0356 0.1901 1.0000
6.250 0.8605 0.01146 0.00499 -0.0345 0.1784 1.0000
6.500 0.8824 0.01177 0.00526 -0.0336 0.1672 1.0000
6.750 0.9048 0.01206 0.00554 -0.0327 0.1565 1.0000
7.000 0.9277 0.01234 0.00583 -0.0319 0.1467 1.0000
7.250 0.9504 0.01266 0.00614 -0.0311 0.1371 1.0000
7.500 0.9728 0.01301 0.00647 -0.0303 0.1269 1.0000
7.750 0.9953 0.01337 0.00682 -0.0295 0.1166 1.0000
8.000 1.0175 0.01377 0.00723 -0.0287 0.1056 1.0000
8.250 1.0397 0.01418 0.00764 -0.0279 0.0934 1.0000
8.500 1.0614 0.01465 0.00805 -0.0270 0.0795 1.0000
8.750 1.0822 0.01519 0.00853 -0.0261 0.0681 1.0000
9.000 1.1029 0.01575 0.00910 -0.0250 0.0612 1.0000
9.250 1.1230 0.01634 0.00971 -0.0240 0.0557 1.0000
9.500 1.1426 0.01695 0.01037 -0.0228 0.0509 1.0000
9.750 1.1644 0.01734 0.01085 -0.0220 0.0471 1.0000
10.000 1.1833 0.01799 0.01150 -0.0208 0.0422 1.0000
10.250 1.2043 0.01842 0.01201 -0.0200 0.0382 1.0000
10.500 1.2213 0.01919 0.01274 -0.0186 0.0318 1.0000
10.750 1.2398 0.01981 0.01339 -0.0174 0.0252 1.0000
11.000 1.2547 0.02062 0.01425 -0.0155 0.0195 1.0000
11.250 1.2666 0.02161 0.01527 -0.0133 0.0162 1.0000
11.500 1.2787 0.02253 0.01625 -0.0112 0.0142 1.0000
11.750 1.2834 0.02396 0.01777 -0.0081 0.0124 1.0000
12.000 1.2940 0.02495 0.01890 -0.0059 0.0117 1.0000
12.250 1.3018 0.02613 0.02020 -0.0035 0.0109 1.0000
12.500 1.3078 0.02744 0.02163 -0.0011 0.0102 1.0000
12.750 1.3100 0.02905 0.02336 0.0015 0.0097 1.0000
13.000 1.3054 0.03121 0.02565 0.0044 0.0092 1.0000
13.250 1.2933 0.03410 0.02873 0.0074 0.0088 1.0000
13.500 1.2920 0.03632 0.03109 0.0091 0.0086 1.0000
13.750 1.2910 0.03867 0.03361 0.0103 0.0084 1.0000
14.000 1.2873 0.04146 0.03656 0.0112 0.0082 1.0000
14.250 1.2815 0.04475 0.04001 0.0114 0.0080 1.0000
14.500 1.2738 0.04858 0.04400 0.0110 0.0078 1.0000
14.750 1.2644 0.05303 0.04862 0.0097 0.0077 1.0000
15.000 1.2536 0.05816 0.05391 0.0076 0.0076 1.0000
15.250 1.2414 0.06389 0.05981 0.0049 0.0075 1.0000
15.500 1.2277 0.07012 0.06620 0.0017 0.0075 1.0000
15.750 1.2126 0.07667 0.07290 -0.0016 0.0074 1.0000
16.000 1.1964 0.08344 0.07981 -0.0049 0.0074 1.0000
16.250 1.1795 0.09036 0.08686 -0.0083 0.0074 1.0000
16.500 1.1622 0.09732 0.09395 -0.0116 0.0074 1.0000
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