NACA 64-008A AIRFOIL (n64008a-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-008A AIRFOIL (n64008a-il) Reynolds number: 500,000 Max Cl/Cd: 44.48 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64008a-il-500000-n5.txt Download as CSV file: xf-n64008a-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64-008A 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.7348 0.08480 0.08271 0.0050 1.0000 0.0049
-9.500 -0.7476 0.07519 0.07311 -0.0050 1.0000 0.0047
-9.250 -0.7664 0.06802 0.06585 -0.0109 1.0000 0.0045
-9.000 -0.7809 0.06175 0.05943 -0.0130 1.0000 0.0045
-8.750 -0.7895 0.05516 0.05264 -0.0140 1.0000 0.0046
-8.500 -0.7953 0.04789 0.04506 -0.0138 1.0000 0.0048
-8.250 -0.8038 0.03794 0.03454 -0.0120 1.0000 0.0052
-8.000 -0.8101 0.02754 0.02319 -0.0087 1.0000 0.0055
-7.750 -0.7952 0.02397 0.01912 -0.0072 1.0000 0.0058
-7.500 -0.7789 0.02086 0.01556 -0.0059 1.0000 0.0062
-7.250 -0.7563 0.01995 0.01453 -0.0054 1.0000 0.0066
-7.000 -0.7329 0.01919 0.01366 -0.0049 1.0000 0.0070
-6.750 -0.7096 0.01827 0.01260 -0.0044 1.0000 0.0075
-6.500 -0.6863 0.01727 0.01142 -0.0037 1.0000 0.0082
-6.250 -0.6620 0.01667 0.01071 -0.0032 1.0000 0.0092
-6.000 -0.6376 0.01614 0.01008 -0.0027 1.0000 0.0098
-5.750 -0.6156 0.01484 0.00861 -0.0018 1.0000 0.0104
-5.500 -0.5948 0.01350 0.00715 -0.0006 1.0000 0.0114
-5.250 -0.5719 0.01286 0.00646 0.0002 1.0000 0.0122
-5.000 -0.5482 0.01247 0.00604 0.0009 1.0000 0.0135
-4.750 -0.5252 0.01197 0.00547 0.0017 1.0000 0.0146
-4.500 -0.5026 0.01145 0.00487 0.0026 1.0000 0.0154
-4.250 -0.4743 0.01097 0.00433 0.0023 0.9973 0.0162
-4.000 -0.4416 0.01054 0.00383 0.0010 0.9921 0.0169
-3.750 -0.4088 0.01011 0.00334 -0.0003 0.9861 0.0181
-3.500 -0.3770 0.00967 0.00283 -0.0013 0.9784 0.0214
-3.250 -0.3449 0.00938 0.00252 -0.0024 0.9701 0.0262
-3.000 -0.3130 0.00909 0.00225 -0.0034 0.9606 0.0392
-2.750 -0.2820 0.00873 0.00202 -0.0043 0.9497 0.0715
-2.500 -0.2533 0.00826 0.00177 -0.0048 0.9365 0.1411
-2.000 -0.2063 0.00649 0.00127 -0.0041 0.9054 0.4959
-1.750 -0.1824 0.00608 0.00120 -0.0033 0.8901 0.5948
-1.500 -0.1588 0.00579 0.00118 -0.0023 0.8752 0.6778
-1.250 -0.1337 0.00566 0.00116 -0.0016 0.8610 0.7223
-1.000 -0.1075 0.00562 0.00112 -0.0011 0.8475 0.7458
-0.750 -0.0809 0.00559 0.00109 -0.0008 0.8343 0.7613
-0.500 -0.0539 0.00559 0.00106 -0.0005 0.8217 0.7736
-0.250 -0.0269 0.00559 0.00104 -0.0003 0.8095 0.7856
0.000 0.0000 0.00558 0.00104 0.0000 0.7974 0.7974
0.250 0.0269 0.00559 0.00104 0.0003 0.7856 0.8095
0.500 0.0539 0.00559 0.00106 0.0005 0.7736 0.8217
0.750 0.0809 0.00559 0.00109 0.0008 0.7613 0.8343
1.000 0.1075 0.00562 0.00112 0.0011 0.7458 0.8475
1.250 0.1337 0.00566 0.00115 0.0016 0.7222 0.8610
1.500 0.1587 0.00579 0.00118 0.0023 0.6779 0.8752
1.750 0.1824 0.00608 0.00120 0.0033 0.5951 0.8901
2.000 0.2061 0.00651 0.00127 0.0041 0.4895 0.9055
2.250 0.2281 0.00746 0.00149 0.0048 0.2881 0.9215
2.500 0.2532 0.00826 0.00177 0.0048 0.1402 0.9365
2.750 0.2820 0.00874 0.00202 0.0043 0.0711 0.9497
3.000 0.3130 0.00909 0.00225 0.0034 0.0393 0.9606
3.250 0.3450 0.00938 0.00252 0.0024 0.0263 0.9701
3.500 0.3771 0.00968 0.00283 0.0013 0.0214 0.9784
3.750 0.4089 0.01011 0.00335 0.0003 0.0181 0.9861
4.000 0.4417 0.01054 0.00384 -0.0010 0.0169 0.9920
4.250 0.4744 0.01097 0.00433 -0.0023 0.0162 0.9973
4.500 0.5027 0.01145 0.00488 -0.0026 0.0155 1.0000
4.750 0.5254 0.01198 0.00547 -0.0017 0.0146 1.0000
5.000 0.5484 0.01246 0.00603 -0.0009 0.0134 1.0000
5.250 0.5720 0.01286 0.00645 -0.0002 0.0122 1.0000
5.500 0.5948 0.01350 0.00715 0.0006 0.0114 1.0000
5.750 0.6155 0.01487 0.00865 0.0018 0.0103 1.0000
6.000 0.6377 0.01614 0.01007 0.0027 0.0098 1.0000
6.250 0.6621 0.01667 0.01071 0.0032 0.0092 1.0000
6.500 0.6863 0.01727 0.01142 0.0037 0.0082 1.0000
6.750 0.7096 0.01826 0.01259 0.0044 0.0075 1.0000
7.000 0.7328 0.01920 0.01367 0.0050 0.0070 1.0000
7.250 0.7562 0.01994 0.01452 0.0054 0.0066 1.0000
7.500 0.7787 0.02084 0.01554 0.0059 0.0062 1.0000
7.750 0.7950 0.02396 0.01910 0.0073 0.0058 1.0000
8.000 0.8099 0.02752 0.02318 0.0088 0.0055 1.0000
8.250 0.8037 0.03782 0.03442 0.0121 0.0052 1.0000
8.500 0.7951 0.04783 0.04499 0.0139 0.0049 1.0000
8.750 0.7892 0.05513 0.05261 0.0141 0.0046 1.0000
9.000 0.7806 0.06171 0.05940 0.0131 0.0045 1.0000
9.250 0.7664 0.06798 0.06581 0.0110 0.0045 1.0000
9.500 0.7477 0.07516 0.07308 0.0051 0.0047 1.0000
9.750 0.7350 0.08480 0.08271 -0.0050 0.0049 1.0000
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Polar data table (+)
Polar graphs
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