BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 200,000 Max Cl/Cd: 55.77 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacnlf-il-200000.txt Download as CSV file: xf-bacnlf-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5506 0.08704 0.08358 -0.0414 1.0014 0.0372
-9.000 -0.5649 0.08171 0.07830 -0.0443 1.0014 0.0371
-8.750 -0.5864 0.07741 0.07403 -0.0454 1.0014 0.0367
-8.500 -0.6142 0.07456 0.07119 -0.0436 1.0014 0.0362
-8.250 -0.6362 0.07173 0.06833 -0.0413 1.0014 0.0362
-8.000 -0.6512 0.06865 0.06518 -0.0393 1.0014 0.0365
-7.750 -0.6619 0.06550 0.06194 -0.0375 1.0014 0.0371
-7.500 -0.6688 0.06228 0.05859 -0.0356 1.0014 0.0381
-7.250 -0.6720 0.05904 0.05517 -0.0339 1.0014 0.0396
-7.000 -0.6710 0.05903 0.05454 -0.0309 1.0014 0.0428
-6.750 -0.6744 0.05341 0.04859 -0.0295 1.0014 0.0437
-6.500 -0.6659 0.04825 0.04355 -0.0291 1.0014 0.0453
-6.250 -0.6548 0.04544 0.04069 -0.0281 1.0014 0.0473
-6.000 -0.6420 0.04290 0.03794 -0.0269 1.0014 0.0508
-5.750 -0.6292 0.04000 0.03449 -0.0257 1.0014 0.0578
-5.500 -0.6123 0.03716 0.03164 -0.0251 1.0014 0.0609
-5.250 -0.5948 0.03498 0.02901 -0.0244 1.0014 0.0713
-5.000 -0.5745 0.03265 0.02662 -0.0239 1.0014 0.0768
-4.750 -0.5286 0.02499 0.01755 -0.0206 1.0014 0.0229
-4.500 -0.5031 0.02442 0.01669 -0.0194 1.0014 0.0209
-4.250 -0.4763 0.02202 0.01409 -0.0190 1.0014 0.0201
-4.000 -0.4501 0.02027 0.01219 -0.0185 1.0014 0.0200
-3.750 -0.4244 0.01899 0.01081 -0.0181 1.0014 0.0204
-3.500 -0.3966 0.01706 0.00885 -0.0184 1.0014 0.0228
-3.250 -0.3679 0.01587 0.00756 -0.0190 1.0014 0.0346
-3.000 -0.3253 0.01237 0.00660 -0.0243 1.0014 0.5942
-2.750 -0.3047 0.01279 0.00712 -0.0224 1.0014 0.6740
-2.500 -0.2843 0.01316 0.00748 -0.0205 1.0014 0.7077
-2.250 -0.2674 0.01362 0.00799 -0.0175 1.0014 0.7451
-2.000 -0.2515 0.01399 0.00843 -0.0142 1.0014 0.7730
-1.750 -0.2305 0.01413 0.00853 -0.0129 1.0014 0.7852
-1.500 -0.2053 0.01416 0.00848 -0.0129 1.0014 0.7905
-1.250 -0.1785 0.01423 0.00848 -0.0132 1.0008 0.7955
-1.000 -0.1413 0.01438 0.00851 -0.0159 0.9979 0.8011
-0.750 -0.1057 0.01453 0.00861 -0.0180 0.9952 0.8054
-0.500 -0.0721 0.01465 0.00869 -0.0198 0.9913 0.8102
-0.250 -0.0349 0.01483 0.00880 -0.0225 0.9881 0.8158
0.000 0.0026 0.01504 0.00903 -0.0249 0.9854 0.8201
0.250 0.0320 0.01509 0.00907 -0.0259 0.9797 0.8253
0.500 0.0695 0.01524 0.00923 -0.0285 0.9756 0.8308
0.750 0.1101 0.01545 0.00949 -0.0315 0.9725 0.8356
1.000 0.1382 0.01547 0.00954 -0.0321 0.9653 0.8416
1.250 0.1756 0.01559 0.00972 -0.0345 0.9614 0.8470
1.500 0.2072 0.01567 0.00988 -0.0357 0.9554 0.8533
1.750 0.2472 0.01566 0.00997 -0.0385 0.9491 0.8592
2.000 0.2816 0.01556 0.00998 -0.0399 0.9403 0.8654
2.250 0.3254 0.01544 0.00997 -0.0432 0.9347 0.8721
2.500 0.3691 0.01483 0.00955 -0.0456 0.9218 0.8778
2.750 0.4254 0.01341 0.00830 -0.0493 0.9024 0.8827
3.000 0.4678 0.01251 0.00758 -0.0511 0.8903 0.8888
3.250 0.5003 0.01155 0.00681 -0.0505 0.8705 0.8972
3.500 0.5279 0.01079 0.00621 -0.0490 0.8457 0.9063
3.750 0.5599 0.01004 0.00555 -0.0483 0.7944 0.9158
4.000 0.5835 0.01051 0.00491 -0.0455 0.5374 0.9262
4.250 0.5782 0.01273 0.00556 -0.0396 0.2234 0.9473
4.500 0.5994 0.01437 0.00648 -0.0393 0.0953 0.9723
4.750 0.6290 0.01519 0.00715 -0.0406 0.0596 0.9986
5.000 0.6501 0.01663 0.00852 -0.0397 0.0344 0.9986
5.250 0.6708 0.01864 0.01047 -0.0387 0.0281 0.9986
5.500 0.6981 0.02007 0.01201 -0.0386 0.0265 0.9986
5.750 0.7272 0.02202 0.01414 -0.0386 0.0256 0.9986
6.000 0.7567 0.02444 0.01683 -0.0384 0.0253 0.9986
6.250 0.7831 0.02652 0.01921 -0.0379 0.0239 0.9986
6.500 0.8068 0.02857 0.02155 -0.0370 0.0224 0.9986
6.750 0.8271 0.03273 0.02629 -0.0349 0.0238 0.9986
7.000 0.8412 0.03733 0.03137 -0.0324 0.0260 0.9986
11.000 0.6050 0.11012 0.10721 -0.0158 0.0441 0.9986
11.250 0.6002 0.11450 0.11157 -0.0172 0.0433 0.9986
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