BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.14 at α=1° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacnlf-il-1000000-n5.txt Download as CSV file: xf-bacnlf-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING HSNLF 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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5435 0.13752 0.13578 -0.0204 1.0014 0.0051
-12.500 -0.5406 0.13331 0.13158 -0.0220 1.0014 0.0051
-7.750 -0.5727 0.02499 0.02133 -0.0699 0.9693 0.0030
-7.500 -0.5517 0.02330 0.01942 -0.0695 0.9663 0.0030
-7.250 -0.5342 0.01996 0.01569 -0.0686 0.9635 0.0028
-7.000 -0.5130 0.01732 0.01269 -0.0680 0.9615 0.0027
-6.500 -0.4666 0.01408 0.00900 -0.0669 0.9572 0.0026
-6.250 -0.4429 0.01298 0.00775 -0.0664 0.9547 0.0026
-6.000 -0.4186 0.01207 0.00671 -0.0661 0.9525 0.0026
-5.750 -0.3937 0.01130 0.00583 -0.0659 0.9504 0.0025
-5.500 -0.3680 0.01065 0.00507 -0.0658 0.9485 0.0025
-5.250 -0.3415 0.01013 0.00446 -0.0658 0.9467 0.0025
-5.000 -0.3153 0.00968 0.00395 -0.0658 0.9446 0.0025
-4.750 -0.2886 0.00933 0.00353 -0.0658 0.9424 0.0025
-4.500 -0.2615 0.00902 0.00317 -0.0659 0.9401 0.0025
-4.250 -0.2342 0.00876 0.00285 -0.0660 0.9378 0.0025
-4.000 -0.2064 0.00854 0.00259 -0.0662 0.9356 0.0026
-3.750 -0.1784 0.00836 0.00237 -0.0664 0.9336 0.0026
-3.500 -0.1508 0.00820 0.00219 -0.0666 0.9313 0.0028
-3.250 -0.1231 0.00805 0.00202 -0.0668 0.9288 0.0035
-3.000 -0.0954 0.00785 0.00186 -0.0670 0.9264 0.0143
-2.750 -0.0678 0.00759 0.00171 -0.0672 0.9240 0.0424
-2.500 -0.0412 0.00698 0.00149 -0.0676 0.9216 0.1618
-2.250 -0.0161 0.00587 0.00117 -0.0681 0.9188 0.3941
-2.000 0.0094 0.00514 0.00112 -0.0682 0.9152 0.5891
-1.750 0.0374 0.00508 0.00113 -0.0684 0.9119 0.6181
-1.500 0.0659 0.00505 0.00112 -0.0686 0.9091 0.6293
-1.250 0.0947 0.00504 0.00107 -0.0689 0.9065 0.6340
-1.000 0.1231 0.00502 0.00106 -0.0692 0.9034 0.6373
-0.750 0.1516 0.00500 0.00106 -0.0695 0.8999 0.6406
-0.500 0.1801 0.00499 0.00104 -0.0697 0.8962 0.6440
-0.250 0.2086 0.00497 0.00101 -0.0699 0.8913 0.6472
0.000 0.2365 0.00495 0.00099 -0.0700 0.8829 0.6502
0.250 0.2645 0.00493 0.00097 -0.0701 0.8738 0.6532
0.500 0.2924 0.00492 0.00095 -0.0702 0.8633 0.6563
0.750 0.3192 0.00496 0.00092 -0.0699 0.8383 0.6594
1.000 0.3426 0.00518 0.00088 -0.0688 0.7718 0.6625
1.250 0.3636 0.00561 0.00096 -0.0674 0.6818 0.6654
1.500 0.3870 0.00595 0.00108 -0.0666 0.6198 0.6684
1.750 0.4051 0.00676 0.00132 -0.0649 0.4752 0.6715
2.000 0.4254 0.00749 0.00157 -0.0637 0.3477 0.6746
2.250 0.4453 0.00831 0.00183 -0.0626 0.2039 0.6776
2.500 0.4678 0.00891 0.00207 -0.0618 0.1081 0.6806
2.750 0.4933 0.00920 0.00225 -0.0616 0.0747 0.6838
3.000 0.5191 0.00946 0.00243 -0.0614 0.0518 0.6870
3.250 0.5452 0.00969 0.00261 -0.0612 0.0370 0.6900
3.500 0.5710 0.00995 0.00281 -0.0610 0.0223 0.6931
3.750 0.5961 0.01028 0.00307 -0.0606 0.0075 0.6964
4.000 0.6220 0.01053 0.00335 -0.0603 0.0054 0.6999
4.250 0.6480 0.01078 0.00363 -0.0601 0.0045 0.7031
4.500 0.6739 0.01101 0.00391 -0.0599 0.0042 0.7062
4.750 0.6994 0.01128 0.00424 -0.0596 0.0041 0.7097
5.000 0.7248 0.01158 0.00459 -0.0592 0.0039 0.7136
5.250 0.7499 0.01191 0.00500 -0.0588 0.0037 0.7173
5.500 0.7747 0.01228 0.00542 -0.0584 0.0035 0.7207
5.750 0.7992 0.01267 0.00589 -0.0579 0.0033 0.7246
6.000 0.8233 0.01313 0.00642 -0.0573 0.0031 0.7287
6.250 0.8462 0.01376 0.00713 -0.0565 0.0028 0.7330
6.500 0.8663 0.01486 0.00841 -0.0551 0.0026 0.7379
6.750 0.8892 0.01555 0.00923 -0.0543 0.0025 0.7432
7.000 0.9121 0.01624 0.01005 -0.0535 0.0024 0.7484
7.250 0.9343 0.01709 0.01105 -0.0526 0.0024 0.7549
7.500 0.9561 0.01804 0.01216 -0.0516 0.0024 0.7621
7.750 0.9773 0.01915 0.01348 -0.0505 0.0023 0.7709
8.000 0.9974 0.02048 0.01504 -0.0493 0.0023 0.7810
8.250 1.0164 0.02200 0.01683 -0.0479 0.0023 0.7930
8.500 1.0334 0.02380 0.01894 -0.0462 0.0023 0.8079
8.750 1.0476 0.02598 0.02150 -0.0440 0.0023 0.8275
9.000 1.0574 0.02861 0.02459 -0.0412 0.0023 0.8539
9.250 1.0603 0.03188 0.02839 -0.0373 0.0023 0.8949
9.500 1.0537 0.03615 0.03325 -0.0322 0.0023 0.9986
9.750 1.0259 0.04479 0.04250 -0.0253 0.0024 0.9986
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Polar data table (+)
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