NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 1,000,000 Max Cl/Cd: 46.78 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc0864c-il-1000000-n5.txt Download as CSV file: xf-rc0864c-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5727 0.09121 0.08950 -0.0083 1.0000 0.0037
-8.750 -0.5743 0.08620 0.08451 -0.0115 1.0000 0.0037
-8.500 -0.5814 0.07899 0.07732 -0.0178 1.0000 0.0036
-8.000 -0.5840 0.06865 0.06691 -0.0263 1.0000 0.0036
-7.750 -0.5837 0.06341 0.06160 -0.0285 1.0000 0.0036
-7.500 -0.5825 0.05849 0.05659 -0.0294 1.0000 0.0035
-7.250 -0.5828 0.05480 0.05282 -0.0291 1.0000 0.0034
-7.000 -0.5876 0.04816 0.04599 -0.0272 1.0000 0.0037
-6.750 -0.5706 0.04438 0.04206 -0.0284 0.9976 0.0037
-6.500 -0.5490 0.04093 0.03845 -0.0300 0.9952 0.0038
-6.250 -0.5276 0.03728 0.03461 -0.0309 0.9919 0.0040
-6.000 -0.5044 0.03366 0.03077 -0.0316 0.9887 0.0043
-5.750 -0.4799 0.02961 0.02644 -0.0319 0.9858 0.0046
-5.250 -0.4334 0.02294 0.01914 -0.0307 0.9759 0.0048
-5.000 -0.4095 0.02062 0.01653 -0.0299 0.9702 0.0049
-4.250 -0.3326 0.01586 0.01100 -0.0280 0.9524 0.0051
-4.000 -0.3070 0.01450 0.00948 -0.0275 0.9463 0.0049
-3.750 -0.2815 0.01339 0.00822 -0.0268 0.9386 0.0047
-3.500 -0.2554 0.01239 0.00707 -0.0262 0.9316 0.0046
-3.250 -0.2295 0.01154 0.00612 -0.0255 0.9229 0.0045
-3.000 -0.2037 0.01080 0.00528 -0.0249 0.9141 0.0045
-2.750 -0.1781 0.01016 0.00456 -0.0242 0.9040 0.0044
-2.500 -0.1525 0.00958 0.00392 -0.0236 0.8939 0.0045
-2.250 -0.1269 0.00910 0.00338 -0.0229 0.8839 0.0046
-2.000 -0.1011 0.00869 0.00292 -0.0224 0.8732 0.0047
-1.750 -0.0749 0.00836 0.00253 -0.0219 0.8620 0.0051
-1.500 -0.0487 0.00807 0.00219 -0.0214 0.8504 0.0055
-1.250 -0.0223 0.00784 0.00194 -0.0211 0.8380 0.0058
-1.000 0.0037 0.00771 0.00174 -0.0206 0.8147 0.0063
-0.750 0.0291 0.00773 0.00161 -0.0199 0.7744 0.0073
-0.500 0.0542 0.00773 0.00145 -0.0192 0.7286 0.0076
-0.250 0.0779 0.00783 0.00126 -0.0183 0.6523 0.0081
0.000 0.1002 0.00829 0.00120 -0.0173 0.5145 0.0088
0.250 0.1222 0.00898 0.00124 -0.0164 0.3406 0.0097
0.500 0.1412 0.01029 0.00148 -0.0153 0.0137 0.0108
0.750 0.1684 0.01031 0.00149 -0.0151 0.0107 0.0129
1.000 0.1926 0.00974 0.00152 -0.0146 0.0099 0.2404
1.250 0.2025 0.00781 0.00154 -0.0114 0.0092 0.8371
1.500 0.2244 0.00777 0.00176 -0.0097 0.0085 0.9147
1.750 0.2499 0.00798 0.00203 -0.0090 0.0079 0.9381
2.000 0.2770 0.00814 0.00221 -0.0086 0.0075 0.9596
2.250 0.3069 0.00835 0.00240 -0.0090 0.0067 0.9713
2.500 0.3362 0.00859 0.00263 -0.0093 0.0063 0.9765
2.750 0.3664 0.00887 0.00289 -0.0099 0.0059 0.9790
3.000 0.3954 0.00927 0.00330 -0.0102 0.0055 0.9820
3.250 0.4235 0.00956 0.00360 -0.0104 0.0052 0.9855
3.500 0.4546 0.00997 0.00402 -0.0112 0.0049 0.9870
3.750 0.4853 0.01046 0.00453 -0.0119 0.0047 0.9884
4.000 0.5151 0.01101 0.00511 -0.0125 0.0045 0.9901
4.250 0.5440 0.01163 0.00575 -0.0129 0.0045 0.9920
4.500 0.5721 0.01232 0.00648 -0.0130 0.0044 0.9940
4.750 0.6009 0.01310 0.00731 -0.0134 0.0044 0.9954
5.000 0.6299 0.01399 0.00826 -0.0138 0.0044 0.9965
5.250 0.6588 0.01498 0.00934 -0.0141 0.0045 0.9978
5.500 0.6872 0.01611 0.01058 -0.0143 0.0045 0.9990
5.750 0.7154 0.01716 0.01175 -0.0145 0.0044 1.0000
6.000 0.7353 0.01802 0.01271 -0.0130 0.0043 1.0000
6.250 0.7550 0.01886 0.01366 -0.0115 0.0042 1.0000
6.500 0.7746 0.01967 0.01455 -0.0101 0.0040 1.0000
6.750 0.7938 0.02057 0.01555 -0.0087 0.0039 1.0000
7.000 0.8122 0.02172 0.01683 -0.0072 0.0039 1.0000
7.250 0.8296 0.02315 0.01845 -0.0055 0.0038 1.0000
7.500 0.8418 0.02555 0.02112 -0.0033 0.0036 1.0000
7.750 0.8621 0.02678 0.02262 -0.0016 0.0031 1.0000
8.000 0.8776 0.02874 0.02481 0.0002 0.0028 1.0000
8.250 0.8939 0.03025 0.02647 0.0016 0.0026 1.0000
8.750 0.9428 0.02914 0.02525 0.0016 0.0020 1.0000
9.000 0.9376 0.03557 0.03228 0.0057 0.0018 1.0000
9.250 0.9307 0.04162 0.03876 0.0092 0.0017 1.0000
9.500 0.9204 0.04754 0.04502 0.0121 0.0016 1.0000
9.750 0.9074 0.05295 0.05068 0.0144 0.0016 1.0000
10.000 0.8895 0.05741 0.05531 0.0168 0.0016 1.0000
10.250 0.8689 0.06192 0.05995 0.0176 0.0017 1.0000
10.500 0.8512 0.06685 0.06500 0.0156 0.0019 1.0000
10.750 0.8364 0.07292 0.07116 0.0108 0.0020 1.0000
11.000 0.8279 0.08170 0.08002 0.0019 0.0021 1.0000
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Polar data table (+)
Polar graphs
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