NACA 64-008A AIRFOIL (n64008a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 64-008A AIRFOIL (n64008a-il) Reynolds number: 200,000 Max Cl/Cd: 35.02 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n64008a-il-200000-n5.txt Download as CSV file: xf-n64008a-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7008 0.08895 0.08561 0.0042 1.0000 0.0120
-9.250 -0.7122 0.07914 0.07584 -0.0049 1.0000 0.0115
-9.000 -0.7340 0.06937 0.06596 -0.0125 1.0000 0.0109
-8.750 -0.7458 0.06318 0.05959 -0.0142 1.0000 0.0106
-8.500 -0.7511 0.05750 0.05370 -0.0148 1.0000 0.0105
-8.250 -0.7526 0.05221 0.04814 -0.0147 1.0000 0.0105
-8.000 -0.7512 0.04715 0.04276 -0.0141 1.0000 0.0105
-7.750 -0.7461 0.04256 0.03782 -0.0132 1.0000 0.0107
-7.500 -0.7366 0.03870 0.03360 -0.0122 1.0000 0.0110
-7.250 -0.7234 0.03549 0.03004 -0.0112 1.0000 0.0114
-7.000 -0.7055 0.03383 0.02813 -0.0106 1.0000 0.0125
-6.750 -0.6871 0.03159 0.02556 -0.0097 1.0000 0.0140
-6.500 -0.6688 0.02840 0.02191 -0.0083 1.0000 0.0147
-6.250 -0.6486 0.02558 0.01863 -0.0069 1.0000 0.0153
-6.000 -0.6264 0.02336 0.01603 -0.0058 1.0000 0.0160
-5.750 -0.6030 0.02187 0.01425 -0.0049 1.0000 0.0169
-5.500 -0.5811 0.01977 0.01192 -0.0041 1.0000 0.0189
-5.250 -0.5582 0.01841 0.01045 -0.0032 1.0000 0.0201
-5.000 -0.5352 0.01725 0.00920 -0.0024 1.0000 0.0212
-4.750 -0.5126 0.01626 0.00808 -0.0014 1.0000 0.0225
-4.500 -0.4903 0.01540 0.00714 -0.0004 1.0000 0.0240
-4.250 -0.4673 0.01482 0.00649 0.0004 1.0000 0.0267
-4.000 -0.4449 0.01420 0.00579 0.0013 1.0000 0.0280
-3.750 -0.4239 0.01334 0.00487 0.0025 1.0000 0.0306
-3.500 -0.4014 0.01279 0.00428 0.0034 1.0000 0.0351
-3.250 -0.3786 0.01231 0.00373 0.0042 1.0000 0.0442
-3.000 -0.3562 0.01178 0.00332 0.0050 1.0000 0.0735
-2.750 -0.3370 0.01058 0.00289 0.0058 1.0000 0.2380
-2.500 -0.3130 0.00894 0.00267 0.0054 0.9945 0.5665
-2.250 -0.2808 0.00860 0.00262 0.0045 0.9869 0.6580
-2.000 -0.2515 0.00836 0.00273 0.0046 0.9784 0.7500
-1.750 -0.2212 0.00827 0.00277 0.0045 0.9691 0.7969
-1.500 -0.1884 0.00822 0.00270 0.0036 0.9596 0.8151
-1.250 -0.1549 0.00818 0.00260 0.0024 0.9503 0.8286
-0.750 -0.0915 0.00811 0.00250 0.0011 0.9281 0.8543
-0.500 -0.0606 0.00808 0.00247 0.0006 0.9163 0.8669
-0.250 -0.0302 0.00807 0.00244 0.0003 0.9043 0.8795
0.000 0.0000 0.00806 0.00244 0.0000 0.8919 0.8919
0.250 0.0302 0.00807 0.00244 -0.0003 0.8795 0.9043
0.500 0.0606 0.00808 0.00247 -0.0006 0.8669 0.9163
0.750 0.0915 0.00811 0.00250 -0.0011 0.8543 0.9281
1.250 0.1549 0.00818 0.00260 -0.0025 0.8287 0.9503
1.500 0.1885 0.00822 0.00270 -0.0036 0.8151 0.9596
1.750 0.2213 0.00827 0.00277 -0.0045 0.7969 0.9690
2.000 0.2516 0.00836 0.00273 -0.0046 0.7499 0.9783
2.250 0.2809 0.00860 0.00262 -0.0045 0.6577 0.9869
2.500 0.3131 0.00894 0.00267 -0.0054 0.5663 0.9944
2.750 0.3371 0.01060 0.00289 -0.0058 0.2360 1.0000
3.000 0.3563 0.01178 0.00332 -0.0050 0.0735 1.0000
3.250 0.3787 0.01231 0.00373 -0.0043 0.0442 1.0000
3.500 0.4015 0.01280 0.00428 -0.0034 0.0351 1.0000
3.750 0.4240 0.01334 0.00487 -0.0025 0.0306 1.0000
4.000 0.4451 0.01420 0.00579 -0.0014 0.0280 1.0000
4.250 0.4675 0.01482 0.00649 -0.0004 0.0267 1.0000
4.500 0.4904 0.01540 0.00715 0.0004 0.0240 1.0000
4.750 0.5127 0.01626 0.00808 0.0014 0.0225 1.0000
5.000 0.5353 0.01726 0.00920 0.0023 0.0212 1.0000
5.250 0.5582 0.01841 0.01045 0.0032 0.0201 1.0000
5.500 0.5812 0.01977 0.01192 0.0040 0.0189 1.0000
5.750 0.6031 0.02185 0.01423 0.0049 0.0169 1.0000
6.000 0.6265 0.02336 0.01603 0.0058 0.0160 1.0000
6.250 0.6486 0.02558 0.01863 0.0069 0.0153 1.0000
6.500 0.6688 0.02840 0.02191 0.0083 0.0146 1.0000
6.750 0.6871 0.03158 0.02555 0.0097 0.0139 1.0000
7.000 0.7055 0.03384 0.02813 0.0106 0.0125 1.0000
7.250 0.7234 0.03548 0.03003 0.0112 0.0114 1.0000
7.500 0.7366 0.03868 0.03358 0.0122 0.0110 1.0000
7.750 0.7461 0.04255 0.03780 0.0132 0.0107 1.0000
8.000 0.7512 0.04715 0.04275 0.0141 0.0105 1.0000
8.250 0.7526 0.05221 0.04813 0.0147 0.0105 1.0000
8.500 0.7511 0.05750 0.05370 0.0148 0.0105 1.0000
8.750 0.7459 0.06316 0.05958 0.0142 0.0106 1.0000
9.000 0.7342 0.06939 0.06598 0.0125 0.0109 1.0000
9.250 0.7124 0.07922 0.07593 0.0048 0.0115 1.0000
9.500 0.7011 0.08899 0.08565 -0.0043 0.0120 1.0000
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Polar data table (+)
Polar graphs
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