BOEING HSNLF AIRFOIL (bacnlf-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: BOEING HSNLF AIRFOIL (bacnlf-il) Reynolds number: 1,000,000 Max Cl/Cd: 88.34 at α=2° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-bacnlf-il-1000000.txt Download as CSV file: xf-bacnlf-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5568 0.07979 0.07822 -0.0431 1.0014 0.0082
-9.250 -0.5775 0.07503 0.07346 -0.0439 1.0014 0.0082
-9.000 -0.5914 0.06932 0.06769 -0.0481 1.0003 0.0082
-8.750 -0.5985 0.06347 0.06172 -0.0544 0.9975 0.0082
-8.500 -0.5948 0.05796 0.05604 -0.0586 0.9949 0.0082
-8.250 -0.5895 0.05320 0.05109 -0.0607 0.9917 0.0082
-8.000 -0.5795 0.04853 0.04620 -0.0626 0.9894 0.0083
-7.750 -0.5655 0.04405 0.04147 -0.0643 0.9878 0.0083
-7.500 -0.5480 0.03983 0.03696 -0.0660 0.9866 0.0083
-5.500 -0.3652 0.01312 0.00787 -0.0678 0.9741 0.0054
-5.250 -0.3345 0.01257 0.00726 -0.0687 0.9734 0.0052
-5.000 -0.3079 0.01131 0.00590 -0.0689 0.9719 0.0050
-4.750 -0.2865 0.01052 0.00501 -0.0679 0.9682 0.0049
-4.500 -0.2590 0.00989 0.00428 -0.0681 0.9660 0.0049
-4.250 -0.2300 0.00942 0.00372 -0.0685 0.9643 0.0049
-4.000 -0.2004 0.00907 0.00331 -0.0691 0.9628 0.0051
-3.750 -0.1704 0.00877 0.00295 -0.0698 0.9615 0.0068
-3.500 -0.1408 0.00846 0.00270 -0.0704 0.9603 0.0236
-3.250 -0.1147 0.00804 0.00248 -0.0705 0.9579 0.0810
-3.000 -0.0896 0.00743 0.00224 -0.0705 0.9550 0.1925
-2.750 -0.0650 0.00623 0.00188 -0.0709 0.9525 0.4289
-2.500 -0.0378 0.00567 0.00179 -0.0713 0.9504 0.5728
-2.250 -0.0087 0.00556 0.00176 -0.0716 0.9485 0.6087
-2.000 0.0194 0.00557 0.00185 -0.0717 0.9463 0.6453
-1.750 0.0462 0.00560 0.00190 -0.0715 0.9429 0.6582
-1.500 0.0742 0.00559 0.00189 -0.0716 0.9401 0.6659
-1.250 0.1029 0.00556 0.00185 -0.0718 0.9377 0.6699
-1.000 0.1319 0.00554 0.00181 -0.0722 0.9355 0.6735
-0.750 0.1607 0.00555 0.00180 -0.0725 0.9333 0.6767
-0.500 0.1878 0.00550 0.00179 -0.0724 0.9295 0.6800
-0.250 0.2155 0.00545 0.00175 -0.0724 0.9250 0.6831
0.000 0.2438 0.00538 0.00167 -0.0725 0.9207 0.6864
0.250 0.2709 0.00535 0.00164 -0.0723 0.9147 0.6897
0.500 0.2987 0.00526 0.00156 -0.0723 0.9088 0.6928
0.750 0.3251 0.00514 0.00147 -0.0718 0.8978 0.6959
1.000 0.3514 0.00503 0.00132 -0.0713 0.8800 0.6991
1.250 0.3788 0.00502 0.00130 -0.0712 0.8670 0.7025
1.500 0.4065 0.00501 0.00130 -0.0712 0.8544 0.7058
1.750 0.4327 0.00503 0.00127 -0.0707 0.8259 0.7089
2.000 0.4576 0.00518 0.00130 -0.0700 0.7813 0.7122
2.250 0.4709 0.00606 0.00146 -0.0669 0.6108 0.7159
2.500 0.4852 0.00716 0.00179 -0.0645 0.4197 0.7193
2.750 0.5042 0.00798 0.00208 -0.0632 0.2796 0.7229
3.000 0.5249 0.00872 0.00237 -0.0621 0.1622 0.7265
3.250 0.5484 0.00922 0.00262 -0.0615 0.0975 0.7303
3.500 0.5728 0.00960 0.00284 -0.0611 0.0577 0.7340
3.750 0.5981 0.00989 0.00307 -0.0608 0.0365 0.7381
4.000 0.6224 0.01032 0.00338 -0.0602 0.0120 0.7425
4.250 0.6477 0.01065 0.00372 -0.0598 0.0080 0.7467
4.500 0.6731 0.01094 0.00410 -0.0594 0.0074 0.7512
4.750 0.6983 0.01127 0.00450 -0.0590 0.0071 0.7562
5.000 0.7232 0.01164 0.00495 -0.0585 0.0067 0.7615
5.250 0.7475 0.01206 0.00548 -0.0578 0.0062 0.7673
5.500 0.7715 0.01255 0.00604 -0.0572 0.0057 0.7737
5.750 0.7944 0.01317 0.00677 -0.0563 0.0053 0.7807
6.250 0.8367 0.01512 0.00903 -0.0537 0.0049 0.7984
6.500 0.8587 0.01614 0.01022 -0.0526 0.0050 0.8099
6.750 0.8808 0.01733 0.01162 -0.0514 0.0051 0.8243
7.250 0.8901 0.03422 0.03043 -0.0401 0.0116 0.8601
7.500 0.8637 0.02349 0.02008 -0.0318 0.0108 0.8419
7.750 0.8714 0.02665 0.02359 -0.0286 0.0102 0.8668
8.000 0.8729 0.02997 0.02727 -0.0247 0.0097 0.9108
8.250 0.8734 0.03369 0.03129 -0.0211 0.0093 0.9986
8.500 0.8717 0.03767 0.03545 -0.0179 0.0091 0.9986
8.750 0.8663 0.04165 0.03961 -0.0146 0.0089 0.9986
9.000 0.8571 0.04550 0.04360 -0.0111 0.0088 0.9986
9.250 0.8394 0.04899 0.04722 -0.0067 0.0087 0.9986
9.500 0.8170 0.05267 0.05102 -0.0027 0.0087 0.9986
9.750 0.7898 0.05721 0.05567 0.0001 0.0087 0.9986
10.000 0.7593 0.06271 0.06129 0.0011 0.0088 0.9986
10.250 0.7226 0.07046 0.06914 -0.0007 0.0091 0.9986
10.500 0.6803 0.08393 0.08268 -0.0099 0.0096 0.9986
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Polar data table (+)
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