LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 79-100 (lwk79100-il) Reynolds number: 50,000 Max Cl/Cd: 27.1 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk79100-il-50000-n5.txt Download as CSV file: xf-lwk79100-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 79-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7553 0.09698 0.08980 0.0030 1.0000 0.0588
-11.000 -0.7754 0.08810 0.08092 -0.0031 1.0000 0.0584
-10.750 -0.7985 0.07998 0.07276 -0.0089 1.0000 0.0578
-10.500 -0.8220 0.07314 0.06584 -0.0136 1.0000 0.0573
-10.250 -0.8459 0.06757 0.06013 -0.0164 1.0000 0.0571
-10.000 -0.8653 0.06295 0.05530 -0.0170 1.0000 0.0571
-9.750 -0.8780 0.05833 0.05033 -0.0172 1.0000 0.0576
-9.500 -0.8842 0.05387 0.04541 -0.0169 1.0000 0.0585
-9.250 -0.8834 0.04972 0.04068 -0.0163 1.0000 0.0595
-9.000 -0.8700 0.04710 0.03806 -0.0158 1.0000 0.0620
-8.750 -0.8566 0.04476 0.03553 -0.0152 1.0000 0.0656
-8.500 -0.8428 0.04187 0.03220 -0.0145 1.0000 0.0690
-8.250 -0.8259 0.03894 0.02873 -0.0137 1.0000 0.0719
-8.000 -0.8063 0.03708 0.02693 -0.0131 1.0000 0.0765
-7.750 -0.7861 0.03514 0.02465 -0.0124 1.0000 0.0825
-7.500 -0.7643 0.03320 0.02260 -0.0116 1.0000 0.0875
-7.250 -0.7427 0.03164 0.02090 -0.0108 1.0000 0.0951
-7.000 -0.7214 0.03015 0.01939 -0.0100 1.0000 0.1040
-6.750 -0.6995 0.02867 0.01780 -0.0091 1.0000 0.1141
-6.500 -0.6787 0.02735 0.01645 -0.0083 1.0000 0.1283
-6.250 -0.6583 0.02603 0.01519 -0.0074 1.0000 0.1458
-6.000 -0.6378 0.02475 0.01398 -0.0066 1.0000 0.1701
-5.750 -0.6177 0.02351 0.01290 -0.0058 1.0000 0.2014
-5.500 -0.5973 0.02236 0.01193 -0.0051 1.0000 0.2421
-5.250 -0.5770 0.02132 0.01116 -0.0042 1.0000 0.2912
-5.000 -0.5561 0.02052 0.01063 -0.0032 1.0000 0.3473
-4.750 -0.5347 0.01997 0.01028 -0.0019 1.0000 0.4034
-4.500 -0.5129 0.01964 0.01012 -0.0004 1.0000 0.4530
-4.250 -0.4907 0.01945 0.00997 0.0011 1.0000 0.4963
-4.000 -0.4682 0.01932 0.00982 0.0026 1.0000 0.5338
-3.750 -0.4457 0.01919 0.00965 0.0040 1.0000 0.5661
-3.500 -0.4232 0.01905 0.00947 0.0055 1.0000 0.5945
-3.250 -0.4007 0.01889 0.00929 0.0070 1.0000 0.6194
-3.000 -0.3784 0.01869 0.00906 0.0084 1.0000 0.6433
-2.750 -0.3563 0.01848 0.00885 0.0098 1.0000 0.6652
-2.500 -0.3347 0.01825 0.00858 0.0112 1.0000 0.6868
-2.250 -0.3136 0.01802 0.00839 0.0127 1.0000 0.7066
-2.000 -0.2938 0.01779 0.00819 0.0141 1.0000 0.7270
-1.750 -0.2753 0.01757 0.00803 0.0157 1.0000 0.7469
-1.500 -0.2585 0.01740 0.00791 0.0174 1.0000 0.7662
-1.250 -0.2213 0.01733 0.00783 0.0153 0.9779 0.7870
-1.000 -0.1781 0.01727 0.00778 0.0122 0.9560 0.8064
-0.750 -0.1349 0.01722 0.00772 0.0093 0.9352 0.8245
-0.500 -0.0907 0.01717 0.00768 0.0063 0.9156 0.8426
-0.250 -0.0454 0.01715 0.00766 0.0031 0.8972 0.8609
0.000 0.0000 0.01714 0.00764 0.0000 0.8794 0.8793
0.250 0.0454 0.01715 0.00766 -0.0031 0.8609 0.8973
0.500 0.0907 0.01717 0.00768 -0.0063 0.8427 0.9156
0.750 0.1349 0.01721 0.00772 -0.0093 0.8245 0.9352
1.000 0.1781 0.01727 0.00777 -0.0122 0.8064 0.9560
1.250 0.2214 0.01733 0.00783 -0.0153 0.7870 0.9779
1.500 0.2584 0.01740 0.00791 -0.0174 0.7662 1.0000
1.750 0.2752 0.01757 0.00803 -0.0157 0.7469 1.0000
2.000 0.2937 0.01779 0.00819 -0.0141 0.7270 1.0000
2.250 0.3136 0.01802 0.00839 -0.0127 0.7066 1.0000
2.500 0.3346 0.01825 0.00858 -0.0111 0.6868 1.0000
2.750 0.3562 0.01848 0.00885 -0.0098 0.6653 1.0000
3.000 0.3784 0.01869 0.00906 -0.0084 0.6433 1.0000
3.250 0.4007 0.01889 0.00929 -0.0070 0.6194 1.0000
3.500 0.4232 0.01905 0.00945 -0.0055 0.5945 1.0000
3.750 0.4457 0.01919 0.00965 -0.0040 0.5661 1.0000
4.000 0.4682 0.01932 0.00981 -0.0026 0.5338 1.0000
4.250 0.4906 0.01945 0.00997 -0.0011 0.4963 1.0000
4.500 0.5129 0.01964 0.01012 0.0004 0.4529 1.0000
4.750 0.5347 0.01997 0.01028 0.0019 0.4035 1.0000
5.000 0.5561 0.02052 0.01062 0.0032 0.3474 1.0000
5.250 0.5771 0.02132 0.01116 0.0042 0.2911 1.0000
5.500 0.5973 0.02236 0.01193 0.0051 0.2421 1.0000
5.750 0.6178 0.02351 0.01290 0.0058 0.2013 1.0000
6.000 0.6378 0.02476 0.01398 0.0066 0.1700 1.0000
6.250 0.6583 0.02603 0.01519 0.0074 0.1456 1.0000
6.500 0.6788 0.02735 0.01645 0.0083 0.1283 1.0000
6.750 0.6996 0.02868 0.01781 0.0091 0.1140 1.0000
7.000 0.7215 0.03015 0.01939 0.0100 0.1039 1.0000
7.250 0.7428 0.03165 0.02091 0.0108 0.0951 1.0000
7.500 0.7645 0.03321 0.02261 0.0116 0.0875 1.0000
7.750 0.7863 0.03515 0.02466 0.0123 0.0825 1.0000
8.000 0.8065 0.03709 0.02694 0.0131 0.0765 1.0000
8.250 0.8261 0.03895 0.02874 0.0136 0.0719 1.0000
8.500 0.8430 0.04188 0.03221 0.0145 0.0690 1.0000
8.750 0.8568 0.04475 0.03552 0.0152 0.0655 1.0000
9.000 0.8704 0.04708 0.03803 0.0158 0.0620 1.0000
9.250 0.8835 0.04975 0.04073 0.0163 0.0595 1.0000
9.500 0.8844 0.05390 0.04544 0.0169 0.0585 1.0000
9.750 0.8784 0.05836 0.05035 0.0171 0.0576 1.0000
10.000 0.8660 0.06296 0.05530 0.0169 0.0572 1.0000
10.250 0.8461 0.06763 0.06019 0.0163 0.0571 1.0000
10.500 0.8232 0.07312 0.06582 0.0136 0.0574 1.0000
10.750 0.7983 0.08015 0.07294 0.0086 0.0578 1.0000
11.000 0.7764 0.08810 0.08092 0.0030 0.0584 1.0000
11.250 0.7564 0.09695 0.08977 -0.0030 0.0588 1.0000
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Polar data table (+)
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