NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 500,000 Max Cl/Cd: 42.67 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rc0864c-il-500000.txt Download as CSV file: xf-rc0864c-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY RC08-64C 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5684 0.08285 0.08051 -0.0159 1.0000 0.0109
-8.000 -0.5746 0.07747 0.07514 -0.0214 1.0000 0.0109
-7.750 -0.5780 0.07246 0.07010 -0.0248 1.0000 0.0109
-7.500 -0.5779 0.06748 0.06505 -0.0274 1.0000 0.0110
-7.250 -0.5762 0.06265 0.06014 -0.0289 1.0000 0.0111
-7.000 -0.5734 0.05787 0.05524 -0.0293 1.0000 0.0113
-6.750 -0.5700 0.05116 0.04827 -0.0285 1.0000 0.0117
-6.500 -0.5371 0.03247 0.02967 -0.0267 1.0000 0.0120
-6.250 -0.5368 0.03008 0.02721 -0.0240 1.0000 0.0121
-6.000 -0.5354 0.02791 0.02497 -0.0213 1.0000 0.0123
-5.750 -0.5330 0.02559 0.02252 -0.0184 1.0000 0.0126
-5.500 -0.5292 0.02318 0.01997 -0.0156 1.0000 0.0130
-5.250 -0.5361 0.03368 0.02986 -0.0137 1.0000 0.0135
-5.000 -0.5279 0.02937 0.02502 -0.0099 1.0000 0.0148
-4.750 -0.5024 0.02762 0.02320 -0.0107 0.9985 0.0156
-4.500 -0.4719 0.02465 0.01980 -0.0117 0.9963 0.0182
-4.250 -0.4407 0.02271 0.01757 -0.0129 0.9942 0.0215
-2.500 -0.2036 0.01305 0.00648 -0.0201 0.9781 0.0241
-2.250 -0.1680 0.01178 0.00524 -0.0214 0.9766 0.0197
-2.000 -0.1338 0.01131 0.00469 -0.0224 0.9730 0.0175
-1.750 -0.1008 0.01052 0.00397 -0.0235 0.9691 0.0168
-1.500 -0.0660 0.00997 0.00344 -0.0249 0.9659 0.0164
-1.250 -0.0307 0.00952 0.00300 -0.0264 0.9631 0.0168
-1.000 -0.0033 0.00921 0.00267 -0.0261 0.9553 0.0178
-0.750 0.0288 0.00892 0.00237 -0.0269 0.9504 0.0207
-0.500 0.0557 0.00868 0.00218 -0.0265 0.9421 0.0298
-0.250 0.0755 0.00704 0.00193 -0.0255 0.9342 0.4476
0.000 0.0835 0.00560 0.00199 -0.0208 0.9224 0.8507
0.250 0.1101 0.00564 0.00224 -0.0192 0.9145 0.9408
0.500 0.1619 0.00594 0.00250 -0.0227 0.8935 0.9780
0.750 0.2214 0.00610 0.00250 -0.0287 0.8556 0.9919
1.000 0.2536 0.00620 0.00234 -0.0292 0.7897 0.9956
1.250 0.2842 0.00666 0.00218 -0.0296 0.6522 0.9975
1.500 0.3124 0.00794 0.00225 -0.0304 0.3695 0.9990
1.750 0.3400 0.00972 0.00263 -0.0316 0.0252 1.0000
2.000 0.3643 0.00992 0.00278 -0.0310 0.0190 1.0000
2.250 0.3885 0.01011 0.00298 -0.0303 0.0175 1.0000
2.500 0.4123 0.01033 0.00323 -0.0295 0.0164 1.0000
2.750 0.4353 0.01066 0.00357 -0.0286 0.0156 1.0000
3.000 0.4576 0.01111 0.00402 -0.0276 0.0153 1.0000
3.250 0.4794 0.01158 0.00449 -0.0264 0.0153 1.0000
3.500 0.5011 0.01199 0.00491 -0.0252 0.0155 1.0000
3.750 0.5225 0.01245 0.00540 -0.0238 0.0160 1.0000
4.000 0.5431 0.01309 0.00608 -0.0222 0.0169 1.0000
4.250 0.5625 0.01414 0.00709 -0.0205 0.0179 1.0000
4.500 0.5852 0.01466 0.00774 -0.0190 0.0204 1.0000
4.750 0.6093 0.01653 0.00956 -0.0177 0.0256 1.0000
7.250 0.8036 0.03167 0.02664 -0.0010 0.0188 1.0000
7.500 0.8224 0.03453 0.02934 -0.0007 0.0182 1.0000
7.750 0.8260 0.03682 0.03243 0.0035 0.0158 1.0000
8.000 0.8396 0.03879 0.03448 0.0047 0.0154 1.0000
8.250 0.8533 0.04145 0.03712 0.0054 0.0152 1.0000
8.500 0.8409 0.04789 0.04444 0.0103 0.0137 1.0000
8.750 0.8421 0.05164 0.04842 0.0121 0.0133 1.0000
9.000 0.8405 0.05530 0.05227 0.0137 0.0131 1.0000
9.250 0.8354 0.05898 0.05612 0.0150 0.0129 1.0000
9.500 0.8237 0.06271 0.05998 0.0166 0.0128 1.0000
9.750 0.8052 0.06711 0.06452 0.0171 0.0128 1.0000
10.000 0.7815 0.07395 0.07150 0.0138 0.0129 1.0000
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Polar data table (+)
Polar graphs
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