BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 500,000 Max Cl/Cd: 64.91 at α=2° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-bacnlf-il-500000-n5.txt Download as CSV file: xf-bacnlf-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6078 0.04687 0.04385 -0.0625 0.9871 0.0050
-8.000 -0.5990 0.04193 0.03859 -0.0641 0.9849 0.0048
-7.750 -0.5909 0.03778 0.03415 -0.0635 0.9805 0.0046
-7.500 -0.5754 0.03341 0.02941 -0.0637 0.9777 0.0044
-7.250 -0.5561 0.02903 0.02461 -0.0639 0.9758 0.0042
-7.000 -0.5338 0.02480 0.01990 -0.0639 0.9744 0.0040
-6.750 -0.5092 0.02094 0.01553 -0.0638 0.9734 0.0038
-6.500 -0.4827 0.01825 0.01244 -0.0638 0.9725 0.0036
-6.250 -0.4627 0.01668 0.01065 -0.0624 0.9690 0.0035
-6.000 -0.4385 0.01539 0.00917 -0.0620 0.9668 0.0035
-5.750 -0.4125 0.01434 0.00799 -0.0621 0.9649 0.0035
-5.500 -0.3852 0.01348 0.00699 -0.0624 0.9634 0.0035
-5.250 -0.3569 0.01276 0.00617 -0.0630 0.9620 0.0035
-5.000 -0.3279 0.01217 0.00548 -0.0637 0.9608 0.0036
-4.750 -0.2983 0.01168 0.00492 -0.0644 0.9598 0.0038
-4.500 -0.2736 0.01134 0.00450 -0.0640 0.9569 0.0040
-4.250 -0.2467 0.01102 0.00410 -0.0641 0.9544 0.0043
-4.000 -0.2184 0.01072 0.00375 -0.0644 0.9524 0.0053
-3.750 -0.1894 0.01041 0.00345 -0.0650 0.9506 0.0129
-3.500 -0.1599 0.01008 0.00318 -0.0657 0.9491 0.0298
-3.250 -0.1303 0.00972 0.00290 -0.0664 0.9477 0.0652
-3.000 -0.1039 0.00904 0.00263 -0.0668 0.9455 0.1766
-2.750 -0.0826 0.00753 0.00223 -0.0670 0.9420 0.4718
-2.500 -0.0566 0.00717 0.00236 -0.0669 0.9395 0.6119
-2.250 -0.0278 0.00718 0.00241 -0.0671 0.9375 0.6420
-2.000 0.0018 0.00717 0.00238 -0.0676 0.9358 0.6524
-1.750 0.0319 0.00713 0.00231 -0.0682 0.9342 0.6564
-1.500 0.0594 0.00713 0.00227 -0.0682 0.9310 0.6603
-1.250 0.0867 0.00711 0.00223 -0.0682 0.9270 0.6637
-1.000 0.1155 0.00706 0.00218 -0.0685 0.9238 0.6668
-0.750 0.1450 0.00702 0.00213 -0.0689 0.9214 0.6700
-0.500 0.1742 0.00700 0.00211 -0.0693 0.9192 0.6736
-0.250 0.2008 0.00702 0.00214 -0.0692 0.9151 0.6770
0.000 0.2288 0.00699 0.00215 -0.0694 0.9117 0.6797
0.250 0.2577 0.00696 0.00213 -0.0697 0.9085 0.6828
0.500 0.2856 0.00691 0.00212 -0.0697 0.9035 0.6864
0.750 0.3129 0.00685 0.00207 -0.0696 0.8957 0.6898
1.000 0.3402 0.00678 0.00204 -0.0694 0.8871 0.6926
1.250 0.3672 0.00666 0.00194 -0.0690 0.8710 0.6957
1.500 0.3936 0.00655 0.00173 -0.0683 0.8306 0.6992
1.750 0.4200 0.00662 0.00166 -0.0678 0.7879 0.7028
2.000 0.4440 0.00684 0.00169 -0.0668 0.7281 0.7059
2.250 0.4586 0.00762 0.00187 -0.0640 0.5880 0.7090
2.500 0.4741 0.00852 0.00218 -0.0618 0.4408 0.7126
2.750 0.4919 0.00944 0.00251 -0.0603 0.3003 0.7165
3.000 0.5097 0.01046 0.00290 -0.0588 0.1460 0.7200
3.250 0.5327 0.01098 0.00318 -0.0582 0.0842 0.7235
3.500 0.5577 0.01128 0.00343 -0.0579 0.0620 0.7273
3.750 0.5830 0.01159 0.00368 -0.0575 0.0444 0.7315
4.000 0.6078 0.01190 0.00397 -0.0571 0.0297 0.7355
4.250 0.6325 0.01224 0.00430 -0.0567 0.0164 0.7400
4.500 0.6569 0.01265 0.00470 -0.0562 0.0089 0.7446
4.750 0.6814 0.01304 0.00516 -0.0556 0.0075 0.7490
5.000 0.7060 0.01340 0.00563 -0.0550 0.0069 0.7542
5.500 0.7541 0.01423 0.00666 -0.0539 0.0055 0.7661
5.750 0.7775 0.01477 0.00730 -0.0531 0.0052 0.7730
6.000 0.7996 0.01547 0.00813 -0.0522 0.0048 0.7803
6.250 0.8206 0.01639 0.00920 -0.0510 0.0046 0.7890
6.500 0.8428 0.01712 0.01009 -0.0500 0.0044 0.7993
6.750 0.8645 0.01798 0.01112 -0.0489 0.0043 0.8110
7.000 0.8857 0.01898 0.01235 -0.0478 0.0041 0.8248
7.250 0.9063 0.02016 0.01378 -0.0464 0.0040 0.8415
7.500 0.9258 0.02151 0.01544 -0.0449 0.0039 0.8637
7.750 0.9427 0.02307 0.01735 -0.0427 0.0038 0.8972
8.000 0.9599 0.02504 0.01975 -0.0407 0.0038 0.9986
8.250 0.9752 0.02779 0.02291 -0.0387 0.0038 0.9986
8.500 0.9850 0.03140 0.02701 -0.0358 0.0038 0.9986
8.750 0.9860 0.03634 0.03251 -0.0318 0.0039 0.9986
9.000 0.9766 0.04276 0.03947 -0.0268 0.0040 0.9986
9.250 0.9615 0.04971 0.04683 -0.0219 0.0041 0.9986
9.500 0.9462 0.05550 0.05290 -0.0178 0.0042 0.9986
9.750 0.9274 0.06011 0.05771 -0.0138 0.0042 0.9986
10.000 0.9062 0.06472 0.06248 -0.0107 0.0043 0.9986
10.250 0.8847 0.06970 0.06759 -0.0094 0.0043 0.9986
10.500 0.8616 0.07578 0.07380 -0.0104 0.0043 0.9986
10.750 0.8394 0.08379 0.08191 -0.0151 0.0043 0.9986
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