NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 200,000 Max Cl/Cd: 33.78 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc0864c-il-200000-n5.txt Download as CSV file: xf-rc0864c-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5629 0.10414 0.10035 -0.0073 1.0000 0.0203
-9.250 -0.5643 0.09869 0.09494 -0.0125 1.0000 0.0206
-9.000 -0.5652 0.09337 0.08965 -0.0173 1.0000 0.0207
-8.750 -0.5652 0.09003 0.08635 -0.0161 1.0000 0.0213
-8.500 -0.5618 0.08725 0.08358 -0.0164 1.0000 0.0219
-8.250 -0.5620 0.08336 0.07972 -0.0190 1.0000 0.0225
-8.000 -0.5664 0.07890 0.07527 -0.0226 1.0000 0.0229
-7.750 -0.5672 0.07462 0.07096 -0.0251 1.0000 0.0237
-7.500 -0.5664 0.07002 0.06629 -0.0275 1.0000 0.0248
-7.250 -0.5655 0.06410 0.05997 -0.0307 1.0000 0.0266
-7.000 -0.5659 0.05929 0.05517 -0.0301 1.0000 0.0273
-6.750 -0.5591 0.05699 0.05291 -0.0290 1.0000 0.0281
-6.250 -0.5439 0.05151 0.04724 -0.0265 1.0000 0.0310
-4.250 -0.4302 0.02522 0.01818 -0.0103 0.9967 0.0160
-4.000 -0.3991 0.02291 0.01564 -0.0112 0.9939 0.0148
-3.750 -0.3651 0.02148 0.01356 -0.0114 0.9903 0.0130
-3.500 -0.3328 0.01964 0.01164 -0.0124 0.9876 0.0126
-3.250 -0.2997 0.01830 0.01013 -0.0134 0.9848 0.0123
-3.000 -0.2680 0.01717 0.00890 -0.0141 0.9807 0.0121
-2.750 -0.2347 0.01618 0.00783 -0.0151 0.9774 0.0121
-2.500 -0.2010 0.01531 0.00692 -0.0162 0.9743 0.0122
-2.250 -0.1707 0.01460 0.00618 -0.0168 0.9688 0.0133
-2.000 -0.1378 0.01381 0.00545 -0.0180 0.9649 0.0148
-1.750 -0.1041 0.01326 0.00488 -0.0193 0.9609 0.0152
-1.500 -0.0740 0.01285 0.00442 -0.0197 0.9541 0.0156
-1.250 -0.0400 0.01249 0.00401 -0.0209 0.9494 0.0163
-1.000 -0.0101 0.01217 0.00366 -0.0212 0.9419 0.0174
-0.750 0.0222 0.01189 0.00337 -0.0220 0.9354 0.0215
-0.500 0.0427 0.01013 0.00311 -0.0214 0.9268 0.4073
-0.250 0.0639 0.00874 0.00351 -0.0185 0.9212 0.8889
0.000 0.1150 0.00892 0.00374 -0.0223 0.9188 0.9535
0.250 0.1665 0.00900 0.00378 -0.0268 0.9094 0.9766
0.500 0.2273 0.00883 0.00348 -0.0326 0.8643 0.9934
0.750 0.2651 0.00875 0.00328 -0.0342 0.8240 0.9989
1.000 0.2882 0.00888 0.00298 -0.0324 0.7237 1.0000
1.250 0.3101 0.00918 0.00287 -0.0309 0.6330 1.0000
1.500 0.3278 0.01025 0.00287 -0.0290 0.4071 1.0000
1.750 0.3425 0.01252 0.00335 -0.0278 0.0225 1.0000
2.000 0.3655 0.01279 0.00358 -0.0269 0.0181 1.0000
2.250 0.3885 0.01303 0.00385 -0.0259 0.0169 1.0000
2.500 0.4112 0.01331 0.00418 -0.0249 0.0161 1.0000
2.750 0.4336 0.01366 0.00458 -0.0239 0.0155 1.0000
3.000 0.4555 0.01408 0.00506 -0.0227 0.0150 1.0000
3.250 0.4766 0.01463 0.00566 -0.0214 0.0145 1.0000
3.500 0.4972 0.01522 0.00628 -0.0201 0.0137 1.0000
3.750 0.5180 0.01577 0.00687 -0.0187 0.0126 1.0000
4.000 0.5381 0.01648 0.00759 -0.0173 0.0120 1.0000
4.250 0.5582 0.01726 0.00838 -0.0158 0.0118 1.0000
4.500 0.5786 0.01813 0.00926 -0.0144 0.0116 1.0000
4.750 0.5995 0.01908 0.01025 -0.0130 0.0115 1.0000
5.000 0.6211 0.02011 0.01133 -0.0118 0.0114 1.0000
5.250 0.6431 0.02120 0.01252 -0.0105 0.0115 1.0000
5.500 0.6652 0.02240 0.01389 -0.0093 0.0116 1.0000
5.750 0.6872 0.02378 0.01551 -0.0079 0.0119 1.0000
6.000 0.7086 0.02540 0.01740 -0.0065 0.0122 1.0000
6.250 0.7290 0.02726 0.01954 -0.0050 0.0127 1.0000
6.500 0.7480 0.02932 0.02190 -0.0034 0.0131 1.0000
6.750 0.7653 0.03161 0.02445 -0.0017 0.0136 1.0000
7.000 0.7811 0.03458 0.02757 -0.0004 0.0141 1.0000
11.500 0.5592 0.11926 0.11562 -0.0025 0.0353 1.0000
11.750 0.5572 0.12294 0.11929 -0.0037 0.0341 1.0000
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Polar data table (+)
Polar graphs
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