BOEING BACXXX AIRFOIL (bacxxx-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING BACXXX AIRFOIL (bacxxx-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.48 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacxxx-il-1000000-n5.txt Download as CSV file: xf-bacxxx-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5319 0.08495 0.08329 -0.0382 1.0000 0.0045
-10.250 -0.5456 0.07694 0.07530 -0.0438 1.0000 0.0044
-10.000 -0.5734 0.06978 0.06811 -0.0485 1.0000 0.0043
-9.750 -0.5942 0.06354 0.06177 -0.0537 0.9980 0.0043
-9.500 -0.6057 0.05784 0.05592 -0.0575 0.9941 0.0043
-9.250 -0.6076 0.05241 0.05030 -0.0593 0.9900 0.0044
-9.000 -0.6014 0.04721 0.04488 -0.0607 0.9877 0.0044
-8.750 -0.5992 0.04101 0.03839 -0.0611 0.9849 0.0045
-8.500 -0.5955 0.03518 0.03221 -0.0600 0.9806 0.0045
-8.250 -0.5947 0.02653 0.02293 -0.0584 0.9771 0.0047
-8.000 -0.5851 0.02153 0.01737 -0.0561 0.9729 0.0047
-7.750 -0.5657 0.01917 0.01471 -0.0551 0.9699 0.0047
-7.500 -0.5428 0.01754 0.01285 -0.0547 0.9678 0.0048
-7.250 -0.5182 0.01631 0.01147 -0.0544 0.9660 0.0049
-7.000 -0.4938 0.01538 0.01042 -0.0541 0.9638 0.0050
-6.750 -0.4709 0.01461 0.00954 -0.0533 0.9604 0.0051
-6.500 -0.4465 0.01388 0.00873 -0.0529 0.9577 0.0053
-6.250 -0.4214 0.01322 0.00800 -0.0525 0.9554 0.0055
-6.000 -0.3957 0.01261 0.00731 -0.0523 0.9533 0.0057
-5.750 -0.3709 0.01205 0.00669 -0.0518 0.9504 0.0059
-5.500 -0.3474 0.01155 0.00612 -0.0511 0.9461 0.0062
-5.250 -0.3227 0.01108 0.00560 -0.0505 0.9421 0.0063
-5.000 -0.2966 0.01064 0.00510 -0.0503 0.9387 0.0065
-4.750 -0.2720 0.01026 0.00468 -0.0497 0.9342 0.0067
-4.500 -0.2470 0.00990 0.00428 -0.0492 0.9294 0.0068
-4.250 -0.2208 0.00956 0.00388 -0.0489 0.9249 0.0069
-4.000 -0.1956 0.00924 0.00353 -0.0484 0.9178 0.0070
-3.750 -0.1704 0.00882 0.00303 -0.0478 0.9086 0.0075
-3.500 -0.1449 0.00855 0.00271 -0.0473 0.8971 0.0078
-3.250 -0.1186 0.00833 0.00243 -0.0470 0.8871 0.0079
-3.000 -0.0917 0.00814 0.00220 -0.0468 0.8793 0.0082
-2.750 -0.0649 0.00798 0.00200 -0.0465 0.8698 0.0087
-2.500 -0.0379 0.00784 0.00182 -0.0463 0.8604 0.0094
-2.250 -0.0110 0.00772 0.00166 -0.0461 0.8496 0.0113
-2.000 0.0154 0.00758 0.00153 -0.0458 0.8366 0.0234
-1.750 0.0416 0.00742 0.00142 -0.0455 0.8231 0.0514
-1.500 0.0588 0.00613 0.00107 -0.0441 0.8056 0.3643
-1.250 0.0801 0.00581 0.00096 -0.0429 0.7676 0.4713
-0.750 0.1189 0.00617 0.00100 -0.0394 0.6110 0.5685
-0.500 0.1409 0.00643 0.00106 -0.0383 0.5429 0.5901
-0.250 0.1657 0.00660 0.00109 -0.0377 0.5012 0.6034
0.000 0.1913 0.00676 0.00112 -0.0374 0.4670 0.6133
0.250 0.2170 0.00690 0.00116 -0.0370 0.4338 0.6208
0.500 0.2428 0.00707 0.00120 -0.0367 0.4007 0.6283
0.750 0.2690 0.00720 0.00124 -0.0364 0.3748 0.6369
1.000 0.2954 0.00732 0.00129 -0.0362 0.3555 0.6455
1.250 0.3221 0.00742 0.00135 -0.0361 0.3380 0.6550
1.500 0.3486 0.00752 0.00140 -0.0359 0.3203 0.6649
1.750 0.3752 0.00762 0.00147 -0.0357 0.3029 0.6750
2.000 0.4019 0.00772 0.00153 -0.0356 0.2891 0.6861
2.250 0.4282 0.00783 0.00161 -0.0354 0.2729 0.6977
2.500 0.4543 0.00795 0.00170 -0.0352 0.2558 0.7098
2.750 0.4808 0.00804 0.00179 -0.0350 0.2439 0.7236
3.000 0.5073 0.00811 0.00189 -0.0348 0.2343 0.7393
3.250 0.5335 0.00820 0.00199 -0.0346 0.2240 0.7577
3.500 0.5596 0.00828 0.00210 -0.0343 0.2136 0.7775
3.750 0.5857 0.00837 0.00222 -0.0341 0.2039 0.7975
4.000 0.6114 0.00848 0.00236 -0.0337 0.1923 0.8172
4.250 0.6364 0.00860 0.00250 -0.0333 0.1787 0.8396
4.500 0.6611 0.00872 0.00266 -0.0327 0.1667 0.8665
4.750 0.6854 0.00883 0.00283 -0.0320 0.1570 0.8966
5.000 0.7098 0.00900 0.00303 -0.0313 0.1436 0.9253
5.250 0.7361 0.00922 0.00322 -0.0311 0.1294 0.9492
5.500 0.7664 0.00945 0.00343 -0.0319 0.1197 0.9663
5.750 0.7980 0.00969 0.00364 -0.0329 0.1118 0.9781
6.000 0.8294 0.00991 0.00387 -0.0340 0.1064 0.9868
6.250 0.8608 0.01016 0.00410 -0.0351 0.1004 0.9932
6.500 0.8929 0.01036 0.00432 -0.0363 0.0964 0.9980
6.750 0.9193 0.01063 0.00457 -0.0363 0.0886 1.0000
7.000 0.9417 0.01089 0.00480 -0.0354 0.0784 1.0000
7.250 0.9629 0.01130 0.00511 -0.0343 0.0634 1.0000
7.500 0.9855 0.01162 0.00540 -0.0335 0.0570 1.0000
7.750 1.0085 0.01193 0.00571 -0.0327 0.0516 1.0000
8.000 1.0320 0.01220 0.00601 -0.0321 0.0475 1.0000
8.250 1.0542 0.01261 0.00638 -0.0313 0.0402 1.0000
8.500 1.0771 0.01296 0.00672 -0.0306 0.0363 1.0000
8.750 1.0996 0.01335 0.00711 -0.0299 0.0318 1.0000
9.000 1.1229 0.01367 0.00745 -0.0293 0.0300 1.0000
9.250 1.1453 0.01406 0.00786 -0.0286 0.0267 1.0000
9.500 1.1673 0.01448 0.00829 -0.0278 0.0232 1.0000
9.750 1.1890 0.01493 0.00874 -0.0270 0.0182 1.0000
10.000 1.2082 0.01560 0.00936 -0.0258 0.0120 1.0000
10.250 1.2281 0.01618 0.00995 -0.0248 0.0093 1.0000
10.500 1.2486 0.01669 0.01050 -0.0238 0.0080 1.0000
10.750 1.2684 0.01724 0.01111 -0.0227 0.0071 1.0000
11.000 1.2872 0.01784 0.01176 -0.0215 0.0062 1.0000
11.250 1.3061 0.01841 0.01239 -0.0203 0.0057 1.0000
11.500 1.3243 0.01895 0.01300 -0.0190 0.0053 1.0000
11.750 1.3408 0.01954 0.01365 -0.0175 0.0049 1.0000
12.000 1.3561 0.02020 0.01437 -0.0158 0.0045 1.0000
12.250 1.3700 0.02093 0.01516 -0.0139 0.0042 1.0000
12.500 1.3819 0.02179 0.01611 -0.0118 0.0038 1.0000
12.750 1.3955 0.02252 0.01693 -0.0100 0.0036 1.0000
13.000 1.4081 0.02330 0.01779 -0.0082 0.0035 1.0000
13.250 1.4197 0.02416 0.01873 -0.0063 0.0033 1.0000
13.500 1.4303 0.02508 0.01973 -0.0044 0.0030 1.0000
13.750 1.4396 0.02610 0.02083 -0.0025 0.0029 1.0000
14.000 1.4474 0.02725 0.02206 -0.0006 0.0027 1.0000
14.250 1.4534 0.02857 0.02347 0.0014 0.0025 1.0000
14.500 1.4567 0.03013 0.02514 0.0034 0.0024 1.0000
14.750 1.4578 0.03195 0.02707 0.0053 0.0023 1.0000
15.000 1.4608 0.03368 0.02891 0.0068 0.0022 1.0000
15.250 1.4623 0.03566 0.03100 0.0081 0.0022 1.0000
15.500 1.4616 0.03796 0.03343 0.0091 0.0021 1.0000
15.750 1.4590 0.04062 0.03622 0.0097 0.0021 1.0000
16.000 1.4544 0.04377 0.03950 0.0098 0.0020 1.0000
16.250 1.4467 0.04756 0.04343 0.0093 0.0020 1.0000
16.500 1.4364 0.05212 0.04814 0.0079 0.0020 1.0000
16.750 1.4224 0.05778 0.05395 0.0054 0.0020 1.0000
17.000 1.4031 0.06480 0.06115 0.0017 0.0020 1.0000
17.250 1.3785 0.07311 0.06963 -0.0026 0.0020 1.0000
17.500 1.3463 0.08272 0.07942 -0.0075 0.0020 1.0000
17.750 1.3082 0.09328 0.09015 -0.0125 0.0020 1.0000
18.000 1.2677 0.10425 0.10128 -0.0177 0.0021 1.0000
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Polar data table (+)
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