BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 500,000 Max Cl/Cd: 72.79 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacxxx-il-500000-n5.txt Download as CSV file: xf-bacxxx-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4081 0.08390 0.08174 -0.0365 1.0000 0.0088
-10.000 -0.4196 0.07851 0.07638 -0.0377 1.0000 0.0088
-9.750 -0.4348 0.07240 0.07029 -0.0394 1.0000 0.0084
-9.500 -0.4597 0.06436 0.06227 -0.0433 1.0000 0.0083
-9.000 -0.5439 0.04416 0.04165 -0.0541 0.9938 0.0072
-8.750 -0.5511 0.03931 0.03663 -0.0545 0.9891 0.0072
-8.500 -0.5462 0.03584 0.03302 -0.0555 0.9867 0.0074
-8.250 -0.5409 0.03266 0.02968 -0.0552 0.9830 0.0075
-8.000 -0.5294 0.02996 0.02685 -0.0554 0.9801 0.0078
-7.750 -0.5153 0.02666 0.02337 -0.0557 0.9780 0.0082
-7.500 -0.5000 0.02267 0.01910 -0.0559 0.9765 0.0085
-7.250 -0.5330 0.02816 0.02351 -0.0502 0.9763 0.0070
-7.000 -0.5168 0.02579 0.02084 -0.0485 0.9718 0.0070
-6.750 -0.4941 0.02318 0.01788 -0.0481 0.9695 0.0070
-6.500 -0.4696 0.02053 0.01487 -0.0480 0.9680 0.0070
-6.250 -0.4432 0.01839 0.01247 -0.0481 0.9669 0.0072
-6.000 -0.4149 0.01715 0.01109 -0.0486 0.9659 0.0075
-5.750 -0.3864 0.01620 0.01005 -0.0490 0.9647 0.0078
-5.500 -0.3658 0.01549 0.00926 -0.0477 0.9603 0.0080
-5.250 -0.3391 0.01472 0.00841 -0.0476 0.9576 0.0083
-5.000 -0.3109 0.01399 0.00760 -0.0479 0.9554 0.0086
-4.750 -0.2823 0.01333 0.00688 -0.0482 0.9536 0.0090
-4.500 -0.2530 0.01283 0.00633 -0.0487 0.9522 0.0096
-4.250 -0.2319 0.01245 0.00590 -0.0474 0.9472 0.0099
-4.000 -0.2061 0.01195 0.00535 -0.0471 0.9434 0.0101
-3.750 -0.1781 0.01138 0.00473 -0.0472 0.9403 0.0103
-3.500 -0.1502 0.01087 0.00417 -0.0473 0.9368 0.0106
-3.250 -0.1266 0.01052 0.00379 -0.0463 0.9296 0.0111
-3.000 -0.0960 0.01014 0.00335 -0.0468 0.9234 0.0120
-2.750 -0.0719 0.00987 0.00304 -0.0458 0.9126 0.0134
-2.500 -0.0447 0.00960 0.00276 -0.0456 0.9044 0.0179
-2.250 -0.0178 0.00932 0.00252 -0.0454 0.8973 0.0367
-2.000 0.0055 0.00861 0.00223 -0.0448 0.8896 0.1666
-1.750 0.0216 0.00707 0.00191 -0.0433 0.8811 0.5135
-1.500 0.0468 0.00688 0.00186 -0.0427 0.8723 0.5673
-1.250 0.0737 0.00673 0.00179 -0.0424 0.8634 0.6018
-1.000 0.1008 0.00663 0.00173 -0.0422 0.8528 0.6289
-0.750 0.1283 0.00658 0.00165 -0.0420 0.8396 0.6408
-0.500 0.1557 0.00655 0.00156 -0.0418 0.8199 0.6490
-0.250 0.1825 0.00656 0.00147 -0.0414 0.7900 0.6578
0.000 0.2069 0.00668 0.00139 -0.0405 0.7377 0.6671
0.250 0.2285 0.00694 0.00137 -0.0390 0.6728 0.6763
0.500 0.2488 0.00731 0.00142 -0.0374 0.5952 0.6865
0.750 0.2704 0.00761 0.00150 -0.0362 0.5371 0.6972
1.000 0.2939 0.00785 0.00158 -0.0354 0.4936 0.7085
1.250 0.3178 0.00806 0.00166 -0.0347 0.4547 0.7209
1.500 0.3423 0.00824 0.00175 -0.0341 0.4204 0.7346
1.750 0.3671 0.00839 0.00184 -0.0336 0.3933 0.7503
2.000 0.3919 0.00854 0.00194 -0.0330 0.3693 0.7676
2.250 0.4170 0.00868 0.00205 -0.0325 0.3479 0.7859
2.500 0.4421 0.00880 0.00216 -0.0321 0.3300 0.8049
2.750 0.4671 0.00891 0.00228 -0.0315 0.3131 0.8251
3.000 0.4921 0.00901 0.00240 -0.0309 0.2985 0.8473
3.500 0.5418 0.00927 0.00271 -0.0297 0.2686 0.8990
3.750 0.5688 0.00945 0.00288 -0.0296 0.2540 0.9242
4.000 0.5991 0.00963 0.00305 -0.0302 0.2413 0.9441
4.250 0.6311 0.00983 0.00324 -0.0313 0.2298 0.9599
4.500 0.6638 0.01004 0.00342 -0.0325 0.2181 0.9725
4.750 0.6966 0.01026 0.00361 -0.0339 0.2065 0.9824
5.000 0.7293 0.01051 0.00383 -0.0352 0.1938 0.9902
5.250 0.7617 0.01082 0.00406 -0.0366 0.1750 0.9967
5.500 0.7900 0.01112 0.00429 -0.0371 0.1584 1.0000
5.750 0.8116 0.01135 0.00451 -0.0360 0.1486 1.0000
6.000 0.8334 0.01161 0.00473 -0.0349 0.1383 1.0000
6.500 0.8781 0.01214 0.00523 -0.0331 0.1204 1.0000
6.750 0.9005 0.01244 0.00552 -0.0323 0.1131 1.0000
7.000 0.9235 0.01272 0.00581 -0.0315 0.1070 1.0000
7.250 0.9461 0.01306 0.00614 -0.0307 0.1003 1.0000
7.500 0.9695 0.01332 0.00645 -0.0300 0.0937 1.0000
7.750 0.9921 0.01368 0.00680 -0.0293 0.0842 1.0000
8.000 1.0140 0.01412 0.00719 -0.0284 0.0709 1.0000
8.250 1.0356 0.01458 0.00762 -0.0276 0.0615 1.0000
8.500 1.0569 0.01508 0.00810 -0.0267 0.0543 1.0000
8.750 1.0790 0.01549 0.00855 -0.0259 0.0489 1.0000
9.000 1.1005 0.01596 0.00903 -0.0250 0.0436 1.0000
9.250 1.1218 0.01643 0.00955 -0.0242 0.0395 1.0000
9.500 1.1427 0.01692 0.01007 -0.0233 0.0357 1.0000
9.750 1.1629 0.01748 0.01064 -0.0222 0.0316 1.0000
10.000 1.1837 0.01794 0.01117 -0.0213 0.0288 1.0000
10.250 1.2026 0.01857 0.01181 -0.0202 0.0243 1.0000
10.500 1.2218 0.01914 0.01242 -0.0190 0.0194 1.0000
10.750 1.2380 0.01994 0.01320 -0.0175 0.0143 1.0000
11.000 1.2530 0.02071 0.01403 -0.0158 0.0117 1.0000
11.250 1.2673 0.02149 0.01488 -0.0139 0.0101 1.0000
11.500 1.2794 0.02243 0.01590 -0.0118 0.0087 1.0000
11.750 1.2931 0.02321 0.01678 -0.0100 0.0080 1.0000
12.000 1.3054 0.02408 0.01776 -0.0080 0.0074 1.0000
12.250 1.3159 0.02508 0.01885 -0.0060 0.0068 1.0000
12.500 1.3242 0.02623 0.02012 -0.0038 0.0063 1.0000
12.750 1.3295 0.02762 0.02162 -0.0013 0.0058 1.0000
13.000 1.3378 0.02879 0.02292 0.0006 0.0056 1.0000
13.250 1.3442 0.03012 0.02441 0.0025 0.0054 1.0000
13.500 1.3488 0.03163 0.02605 0.0044 0.0051 1.0000
13.750 1.3517 0.03334 0.02790 0.0062 0.0049 1.0000
14.000 1.3531 0.03526 0.02995 0.0078 0.0047 1.0000
14.250 1.3527 0.03746 0.03229 0.0091 0.0046 1.0000
14.500 1.3503 0.04001 0.03498 0.0100 0.0044 1.0000
14.750 1.3453 0.04304 0.03816 0.0105 0.0043 1.0000
15.000 1.3377 0.04671 0.04198 0.0102 0.0042 1.0000
15.250 1.3270 0.05118 0.04662 0.0091 0.0041 1.0000
15.500 1.3132 0.05670 0.05231 0.0067 0.0041 1.0000
15.750 1.2968 0.06328 0.05907 0.0033 0.0040 1.0000
16.000 1.2772 0.07081 0.06679 -0.0008 0.0040 1.0000
16.250 1.2546 0.07898 0.07513 -0.0051 0.0040 1.0000
16.500 1.2297 0.08739 0.08370 -0.0092 0.0041 1.0000
16.750 1.2038 0.09597 0.09242 -0.0133 0.0041 1.0000
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