lrn1007 (lrn1007-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: lrn1007 (lrn1007-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.32 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lrn1007-il-1000000.txt Download as CSV file: xf-lrn1007-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: lrn1007
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
------ -------- --------- --------- -------- -------- --------
-2.500 0.1830 0.02725 0.02375 -0.0972 0.7864 0.0015
-2.250 0.2122 0.02519 0.02156 -0.0978 0.7876 0.0019
-2.000 0.2414 0.02331 0.01953 -0.0979 0.7871 0.0024
-1.750 0.2714 0.02176 0.01785 -0.0978 0.7866 0.0031
-1.500 0.3027 0.02093 0.01689 -0.0972 0.7860 0.0035
-1.250 0.3320 0.01938 0.01519 -0.0970 0.7853 0.0036
-1.000 0.3611 0.01782 0.01346 -0.0967 0.7843 0.0036
-0.750 0.3897 0.01620 0.01168 -0.0964 0.7828 0.0036
-0.500 0.4181 0.01464 0.00994 -0.0961 0.7807 0.0036
-0.250 0.4465 0.01301 0.00813 -0.0956 0.7787 0.0037
0.000 0.4743 0.01105 0.00593 -0.0951 0.7766 0.0044
2.250 0.7177 0.00708 0.00154 -0.0947 0.7510 0.0130
2.500 0.7450 0.00699 0.00140 -0.0948 0.7468 0.0113
2.750 0.7703 0.00605 0.00121 -0.0947 0.7344 0.4914
3.000 0.7720 0.00793 0.00156 -0.0905 0.3284 0.6260
3.250 0.7740 0.00968 0.00254 -0.0867 0.0259 0.8419
3.500 0.8106 0.00972 0.00275 -0.0889 0.0046 1.0000
3.750 0.8363 0.00996 0.00307 -0.0885 0.0070 1.0000
4.000 0.8626 0.01019 0.00349 -0.0879 0.0096 1.0000
4.250 0.8856 0.01082 0.00427 -0.0868 0.0078 1.0000
4.750 0.9232 0.01299 0.00665 -0.0835 0.0025 1.0000
5.000 0.9411 0.01422 0.00792 -0.0817 0.0019 1.0000
5.250 0.9575 0.01606 0.00979 -0.0797 0.0014 1.0000
7.000 1.1020 0.03635 0.03177 -0.0685 0.0012 1.0000
7.250 1.1136 0.03938 0.03513 -0.0657 0.0012 1.0000
7.500 1.1273 0.04229 0.03840 -0.0629 0.0011 1.0000
7.750 1.1346 0.04587 0.04225 -0.0600 0.0011 1.0000
8.000 1.1387 0.04957 0.04619 -0.0571 0.0011 1.0000
8.250 1.1396 0.05326 0.05011 -0.0540 0.0011 1.0000
8.500 1.1369 0.05698 0.05403 -0.0509 0.0011 1.0000
8.750 1.1309 0.06052 0.05775 -0.0478 0.0011 1.0000
9.000 1.1181 0.06352 0.06090 -0.0439 0.0011 1.0000
9.250 1.1018 0.06650 0.06401 -0.0404 0.0011 1.0000
9.500 1.0855 0.06992 0.06755 -0.0382 0.0011 1.0000
9.750 1.0684 0.07378 0.07153 -0.0369 0.0011 1.0000
10.000 1.0513 0.07809 0.07595 -0.0365 0.0011 1.0000
10.250 1.0343 0.08292 0.08089 -0.0371 0.0011 1.0000
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Polar data table (+)
Polar graphs
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