BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 200,000 Max Cl/Cd: 55.21 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacxxx-il-200000-n5.txt Download as CSV file: xf-bacxxx-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5072 0.08600 0.08239 -0.0449 1.0000 0.0263
-9.500 -0.5211 0.08140 0.07778 -0.0470 1.0000 0.0262
-9.250 -0.5375 0.07767 0.07404 -0.0475 1.0000 0.0261
-9.000 -0.5552 0.07468 0.07106 -0.0460 1.0000 0.0259
-8.750 -0.5758 0.07231 0.06871 -0.0426 1.0000 0.0256
-8.500 -0.5951 0.06982 0.06617 -0.0392 1.0000 0.0256
-8.250 -0.6164 0.06849 0.06458 -0.0350 1.0000 0.0264
-8.000 -0.6260 0.06621 0.06215 -0.0317 1.0000 0.0266
-7.750 -0.6322 0.06370 0.05947 -0.0286 1.0000 0.0266
-7.500 -0.6265 0.06029 0.05583 -0.0280 0.9982 0.0267
-7.250 -0.6156 0.05424 0.04972 -0.0292 0.9960 0.0260
-7.000 -0.6081 0.04382 0.03862 -0.0279 0.9922 0.0140
-6.750 -0.5910 0.04034 0.03487 -0.0280 0.9894 0.0137
-6.500 -0.5698 0.03703 0.03124 -0.0283 0.9870 0.0134
-6.250 -0.5488 0.03399 0.02786 -0.0280 0.9841 0.0132
-6.000 -0.5262 0.03114 0.02466 -0.0276 0.9811 0.0131
-5.750 -0.5002 0.02848 0.02163 -0.0275 0.9788 0.0130
-5.500 -0.4719 0.02611 0.01889 -0.0276 0.9771 0.0131
-5.250 -0.4447 0.02418 0.01665 -0.0274 0.9750 0.0134
-5.000 -0.4185 0.02285 0.01500 -0.0269 0.9721 0.0140
-4.750 -0.3914 0.02152 0.01361 -0.0272 0.9697 0.0151
-4.500 -0.3620 0.02051 0.01250 -0.0277 0.9678 0.0158
-4.250 -0.3319 0.01937 0.01127 -0.0282 0.9662 0.0161
-4.000 -0.3025 0.01839 0.01023 -0.0287 0.9645 0.0164
-3.750 -0.2800 0.01761 0.00939 -0.0277 0.9603 0.0168
-3.500 -0.2528 0.01687 0.00861 -0.0278 0.9573 0.0174
-3.250 -0.2232 0.01622 0.00789 -0.0284 0.9549 0.0183
-3.000 -0.1915 0.01568 0.00726 -0.0294 0.9530 0.0195
-2.750 -0.1658 0.01515 0.00666 -0.0292 0.9488 0.0220
-2.500 -0.1356 0.01472 0.00620 -0.0297 0.9435 0.0289
-2.250 -0.0952 0.01397 0.00559 -0.0324 0.9392 0.0768
-2.000 -0.0779 0.01162 0.00523 -0.0315 0.9303 0.5704
-1.750 -0.0403 0.01120 0.00503 -0.0330 0.9246 0.6456
-1.500 -0.0143 0.01097 0.00488 -0.0321 0.9154 0.6838
-1.250 0.0201 0.01073 0.00463 -0.0331 0.9100 0.7021
-1.000 0.0462 0.01060 0.00448 -0.0326 0.9019 0.7125
-0.750 0.0781 0.01042 0.00428 -0.0332 0.8963 0.7232
-0.500 0.1046 0.01030 0.00417 -0.0328 0.8880 0.7350
-0.250 0.1364 0.01012 0.00399 -0.0333 0.8812 0.7475
0.000 0.1625 0.01001 0.00390 -0.0327 0.8707 0.7614
0.250 0.1910 0.00987 0.00379 -0.0326 0.8598 0.7761
0.500 0.2202 0.00971 0.00366 -0.0325 0.8472 0.7916
0.750 0.2495 0.00956 0.00353 -0.0324 0.8306 0.8079
1.000 0.2807 0.00940 0.00337 -0.0327 0.8095 0.8248
1.250 0.3112 0.00929 0.00325 -0.0328 0.7789 0.8428
1.500 0.3434 0.00925 0.00309 -0.0332 0.7327 0.8611
1.750 0.3732 0.00940 0.00297 -0.0330 0.6675 0.8794
2.000 0.3986 0.00980 0.00300 -0.0322 0.5873 0.8988
2.250 0.4236 0.01027 0.00314 -0.0316 0.5217 0.9187
2.500 0.4514 0.01069 0.00332 -0.0317 0.4714 0.9367
2.750 0.4821 0.01106 0.00350 -0.0325 0.4322 0.9523
3.000 0.5139 0.01140 0.00370 -0.0336 0.3991 0.9664
3.250 0.5470 0.01173 0.00389 -0.0351 0.3722 0.9786
3.500 0.5814 0.01202 0.00410 -0.0369 0.3502 0.9891
3.750 0.6170 0.01232 0.00431 -0.0389 0.3294 0.9979
4.000 0.6410 0.01258 0.00452 -0.0385 0.3128 1.0000
4.250 0.6613 0.01282 0.00471 -0.0372 0.2985 1.0000
4.500 0.6820 0.01306 0.00491 -0.0359 0.2850 1.0000
4.750 0.7027 0.01332 0.00513 -0.0347 0.2708 1.0000
5.000 0.7237 0.01360 0.00539 -0.0335 0.2567 1.0000
5.250 0.7451 0.01388 0.00565 -0.0324 0.2433 1.0000
5.500 0.7669 0.01417 0.00593 -0.0314 0.2313 1.0000
5.750 0.7888 0.01447 0.00622 -0.0305 0.2189 1.0000
6.000 0.8107 0.01479 0.00655 -0.0295 0.2058 1.0000
6.250 0.8327 0.01513 0.00687 -0.0286 0.1931 1.0000
6.500 0.8545 0.01550 0.00722 -0.0277 0.1801 1.0000
6.750 0.8763 0.01589 0.00759 -0.0268 0.1670 1.0000
7.000 0.8982 0.01628 0.00801 -0.0259 0.1554 1.0000
7.250 0.9204 0.01667 0.00843 -0.0251 0.1441 1.0000
7.500 0.9423 0.01709 0.00888 -0.0243 0.1330 1.0000
7.750 0.9638 0.01754 0.00935 -0.0234 0.1232 1.0000
8.000 0.9845 0.01807 0.00987 -0.0224 0.1140 1.0000
8.250 1.0058 0.01856 0.01046 -0.0215 0.1051 1.0000
8.500 1.0263 0.01912 0.01107 -0.0205 0.0967 1.0000
8.750 1.0461 0.01972 0.01172 -0.0194 0.0877 1.0000
9.000 1.0665 0.02028 0.01238 -0.0184 0.0795 1.0000
9.250 1.0855 0.02094 0.01306 -0.0172 0.0714 1.0000
9.500 1.1030 0.02170 0.01382 -0.0159 0.0629 1.0000
9.750 1.1208 0.02243 0.01461 -0.0147 0.0558 1.0000
10.000 1.1365 0.02329 0.01552 -0.0131 0.0509 1.0000
10.250 1.1540 0.02396 0.01635 -0.0118 0.0461 1.0000
10.500 1.1674 0.02486 0.01729 -0.0099 0.0415 1.0000
10.750 1.1824 0.02563 0.01821 -0.0082 0.0376 1.0000
11.000 1.1947 0.02658 0.01922 -0.0064 0.0333 1.0000
11.250 1.2063 0.02759 0.02038 -0.0044 0.0291 1.0000
11.500 1.2162 0.02873 0.02160 -0.0024 0.0248 1.0000
11.750 1.2237 0.03003 0.02304 -0.0002 0.0217 1.0000
12.000 1.2309 0.03137 0.02451 0.0019 0.0190 1.0000
12.250 1.2342 0.03300 0.02621 0.0042 0.0171 1.0000
12.500 1.2380 0.03463 0.02801 0.0062 0.0156 1.0000
12.750 1.2404 0.03643 0.02996 0.0080 0.0144 1.0000
13.000 1.2395 0.03858 0.03223 0.0097 0.0134 1.0000
13.250 1.2338 0.04128 0.03507 0.0112 0.0127 1.0000
13.500 1.2274 0.04428 0.03824 0.0121 0.0123 1.0000
13.750 1.2211 0.04755 0.04171 0.0125 0.0119 1.0000
14.000 1.2128 0.05139 0.04575 0.0120 0.0116 1.0000
14.250 1.2026 0.05589 0.05045 0.0107 0.0114 1.0000
14.500 1.1906 0.06113 0.05588 0.0085 0.0112 1.0000
14.750 1.1770 0.06712 0.06207 0.0055 0.0110 1.0000
15.000 1.1616 0.07374 0.06887 0.0020 0.0110 1.0000
15.250 1.1446 0.08078 0.07608 -0.0018 0.0109 1.0000
15.500 1.1265 0.08809 0.08355 -0.0055 0.0109 1.0000
15.750 1.1078 0.09554 0.09114 -0.0093 0.0109 1.0000
16.000 1.0890 0.10305 0.09879 -0.0130 0.0109 1.0000
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