BOEING AIRFOIL J (no closed TE) (bacj-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: BOEING AIRFOIL J (no closed TE) (bacj-il) Reynolds number: 200,000 Max Cl/Cd: -1 at α=-100° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacj-il-200000-n5.txt Download as CSV file: xf-bacj-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: BOEING AIRFOIL J
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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7503 0.07341 0.06901 -0.0578 1.0000 0.0226
-12.750 -0.7715 0.06753 0.06312 -0.0607 1.0000 0.0232
-12.500 -0.8031 0.06095 0.05633 -0.0641 1.0000 0.0232
-12.250 -0.8349 0.05540 0.05056 -0.0655 1.0000 0.0230
-12.000 -0.8575 0.05167 0.04657 -0.0651 1.0000 0.0226
-11.750 -0.8770 0.04851 0.04326 -0.0638 1.0000 0.0228
-11.500 -0.8795 0.04723 0.04205 -0.0622 1.0000 0.0234
-11.250 -0.9040 0.04415 0.03868 -0.0595 1.0000 0.0231
-11.000 -0.9089 0.04309 0.03762 -0.0571 1.0000 0.0236
-10.750 -0.9232 0.04135 0.03574 -0.0537 0.9999 0.0238
-10.500 -0.9231 0.03901 0.03310 -0.0530 0.9963 0.0236
-10.250 -0.9171 0.03798 0.03198 -0.0515 0.9931 0.0243
-10.000 -0.9149 0.03600 0.02972 -0.0494 0.9894 0.0241
-9.750 -0.9028 0.03510 0.02871 -0.0483 0.9865 0.0248
-9.500 -0.8912 0.03311 0.02646 -0.0474 0.9842 0.0247
-9.250 -0.8764 0.03216 0.02534 -0.0464 0.9819 0.0261
-9.000 -0.8651 0.03096 0.02397 -0.0445 0.9784 0.0264
-8.750 -0.8507 0.02940 0.02220 -0.0431 0.9757 0.0264
-8.500 -0.8336 0.02863 0.02122 -0.0419 0.9732 0.0283
-8.250 -0.8129 0.02748 0.01991 -0.0415 0.9713 0.0285
-8.000 -0.7895 0.02659 0.01885 -0.0413 0.9696 0.0292
-7.750 -0.7733 0.02567 0.01782 -0.0397 0.9669 0.0290
-7.500 -0.7619 0.02434 0.01647 -0.0374 0.9638 0.0303
-7.250 -0.7441 0.02357 0.01564 -0.0360 0.9610 0.0312
-7.000 -0.7231 0.02282 0.01484 -0.0353 0.9584 0.0324
-6.750 -0.7010 0.02216 0.01410 -0.0347 0.9565 0.0341
-6.500 -0.6772 0.02160 0.01346 -0.0344 0.9550 0.0348
-6.250 -0.6624 0.02102 0.01281 -0.0322 0.9519 0.0349
-6.000 -0.6468 0.02063 0.01234 -0.0300 0.9481 0.0369
-5.750 -0.6307 0.01984 0.01157 -0.0282 0.9450 0.0406
-5.500 -0.6087 0.01941 0.01107 -0.0274 0.9427 0.0438
-5.250 -0.5836 0.01899 0.01057 -0.0270 0.9408 0.0457
-5.000 -0.5582 0.01854 0.01010 -0.0268 0.9393 0.0494
-4.750 -0.5500 0.01813 0.00971 -0.0231 0.9341 0.0546
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Polar data table (+)
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