NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY RC08-64C AIRFOIL (rc0864c-il) Reynolds number: 500,000 Max Cl/Cd: 40.3 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rc0864c-il-500000-n5.txt Download as CSV file: xf-rc0864c-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5638 0.08390 0.08154 -0.0153 1.0000 0.0073
-8.250 -0.5681 0.07842 0.07608 -0.0208 1.0000 0.0073
-8.000 -0.5731 0.07325 0.07089 -0.0246 1.0000 0.0073
-7.750 -0.5730 0.06770 0.06527 -0.0277 1.0000 0.0074
-7.500 -0.5710 0.06239 0.05986 -0.0294 1.0000 0.0074
-7.250 -0.5677 0.05721 0.05454 -0.0298 1.0000 0.0074
-7.000 -0.5643 0.05213 0.04929 -0.0289 1.0000 0.0075
-6.750 -0.5610 0.04750 0.04446 -0.0270 1.0000 0.0075
-6.500 -0.5580 0.04358 0.04029 -0.0244 1.0000 0.0075
-6.250 -0.5543 0.04037 0.03684 -0.0214 1.0000 0.0075
-6.000 -0.5373 0.03594 0.03224 -0.0222 0.9973 0.0077
-5.750 -0.5136 0.03326 0.02941 -0.0236 0.9947 0.0078
-5.500 -0.4896 0.03105 0.02703 -0.0245 0.9913 0.0082
-5.250 -0.4628 0.02856 0.02429 -0.0253 0.9883 0.0090
-5.000 -0.4306 0.02630 0.02123 -0.0250 0.9857 0.0101
-4.750 -0.4065 0.02312 0.01773 -0.0248 0.9813 0.0103
-4.500 -0.3784 0.02077 0.01532 -0.0256 0.9784 0.0105
-4.250 -0.3485 0.01907 0.01343 -0.0263 0.9758 0.0108
-3.750 -0.2898 0.01611 0.00996 -0.0258 0.9671 0.0072
-3.500 -0.2595 0.01480 0.00852 -0.0263 0.9636 0.0070
-3.250 -0.2312 0.01379 0.00741 -0.0262 0.9584 0.0068
-3.000 -0.2028 0.01292 0.00645 -0.0261 0.9527 0.0067
-2.750 -0.1731 0.01215 0.00561 -0.0263 0.9480 0.0067
-2.500 -0.1470 0.01151 0.00492 -0.0258 0.9403 0.0067
-2.250 -0.1192 0.01093 0.00431 -0.0256 0.9336 0.0069
-2.000 -0.0932 0.01048 0.00383 -0.0250 0.9247 0.0071
-1.750 -0.0658 0.01016 0.00347 -0.0247 0.9165 0.0075
-1.500 -0.0411 0.00956 0.00290 -0.0240 0.9067 0.0082
-1.250 -0.0146 0.00929 0.00263 -0.0237 0.8973 0.0095
-1.000 0.0122 0.00907 0.00238 -0.0233 0.8876 0.0100
-0.750 0.0384 0.00881 0.00210 -0.0228 0.8763 0.0104
-0.500 0.0645 0.00862 0.00183 -0.0222 0.8589 0.0111
-0.250 0.0890 0.00855 0.00161 -0.0211 0.8179 0.0120
0.000 0.1139 0.00855 0.00144 -0.0202 0.7775 0.0145
0.250 0.1350 0.00802 0.00130 -0.0189 0.7241 0.2122
0.500 0.1398 0.00624 0.00121 -0.0146 0.6503 0.7878
0.750 0.1579 0.00642 0.00138 -0.0119 0.5602 0.8939
1.000 0.1788 0.00758 0.00169 -0.0105 0.3247 0.9424
1.250 0.2009 0.00915 0.00210 -0.0100 0.0141 0.9554
1.500 0.2363 0.00940 0.00234 -0.0115 0.0121 0.9715
1.750 0.2775 0.00972 0.00268 -0.0143 0.0109 0.9799
2.000 0.3092 0.00994 0.00291 -0.0151 0.0105 0.9828
2.250 0.3394 0.01021 0.00317 -0.0157 0.0101 0.9860
2.500 0.3720 0.01052 0.00347 -0.0169 0.0089 0.9877
2.750 0.4027 0.01108 0.00401 -0.0177 0.0080 0.9898
3.000 0.4337 0.01148 0.00441 -0.0185 0.0076 0.9923
3.250 0.4636 0.01192 0.00486 -0.0191 0.0073 0.9948
3.500 0.4946 0.01246 0.00542 -0.0199 0.0070 0.9964
3.750 0.5247 0.01307 0.00606 -0.0206 0.0067 0.9982
4.000 0.5545 0.01376 0.00678 -0.0211 0.0066 0.9999
4.250 0.5754 0.01442 0.00748 -0.0198 0.0065 1.0000
4.500 0.5960 0.01515 0.00825 -0.0183 0.0065 1.0000
4.750 0.6168 0.01595 0.00912 -0.0169 0.0065 1.0000
5.000 0.6379 0.01685 0.01010 -0.0154 0.0066 1.0000
5.250 0.6590 0.01785 0.01120 -0.0140 0.0067 1.0000
5.500 0.6800 0.01898 0.01248 -0.0126 0.0068 1.0000
5.750 0.7007 0.02026 0.01392 -0.0111 0.0070 1.0000
6.000 0.7207 0.02171 0.01554 -0.0095 0.0072 1.0000
6.250 0.7396 0.02338 0.01739 -0.0079 0.0074 1.0000
6.500 0.7576 0.02508 0.01931 -0.0062 0.0075 1.0000
6.750 0.7753 0.02660 0.02114 -0.0042 0.0072 1.0000
7.000 0.7923 0.02831 0.02312 -0.0024 0.0067 1.0000
7.250 0.8077 0.03030 0.02537 -0.0005 0.0065 1.0000
7.500 0.8200 0.03317 0.02858 0.0018 0.0066 1.0000
7.750 0.8297 0.03648 0.03222 0.0042 0.0067 1.0000
8.000 0.8362 0.04019 0.03626 0.0066 0.0069 1.0000
8.250 0.8393 0.04420 0.04058 0.0090 0.0071 1.0000
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Polar data table (+)
Polar graphs
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