RAE 102 AIRFOIL (rae102-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 102 AIRFOIL (rae102-il) Reynolds number: 500,000 Max Cl/Cd: 54.7 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae102-il-500000-n5.txt Download as CSV file: xf-rae102-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 102 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
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9098 0.08572 0.08312 -0.0101 1.0000 0.0063
-14.000 -0.9411 0.07383 0.07108 -0.0179 1.0000 0.0061
-13.750 -0.9696 0.06399 0.06104 -0.0247 1.0000 0.0062
-13.500 -0.9887 0.05711 0.05399 -0.0291 1.0000 0.0062
-13.250 -1.0106 0.05065 0.04731 -0.0326 1.0000 0.0061
-13.000 -1.0257 0.04584 0.04230 -0.0344 1.0000 0.0061
-12.750 -1.0366 0.04204 0.03829 -0.0351 1.0000 0.0062
-12.500 -1.0439 0.03902 0.03508 -0.0348 1.0000 0.0062
-12.250 -1.0504 0.03638 0.03223 -0.0337 1.0000 0.0063
-12.000 -1.0609 0.03362 0.02925 -0.0314 1.0000 0.0064
-11.750 -1.0645 0.03159 0.02702 -0.0287 1.0000 0.0064
-11.500 -1.0660 0.02991 0.02520 -0.0256 1.0000 0.0066
-11.250 -1.0578 0.02891 0.02410 -0.0235 1.0000 0.0068
-11.000 -1.0474 0.02772 0.02280 -0.0217 1.0000 0.0070
-10.750 -1.0334 0.02683 0.02181 -0.0202 1.0000 0.0072
-10.500 -1.0202 0.02563 0.02045 -0.0186 1.0000 0.0075
-10.250 -1.0056 0.02450 0.01917 -0.0171 1.0000 0.0077
-10.000 -0.9908 0.02324 0.01775 -0.0155 1.0000 0.0079
-9.750 -0.9744 0.02216 0.01651 -0.0141 1.0000 0.0082
-9.500 -0.9570 0.02118 0.01539 -0.0127 1.0000 0.0086
-9.250 -0.9394 0.02018 0.01426 -0.0113 1.0000 0.0088
-9.000 -0.9205 0.01936 0.01331 -0.0101 1.0000 0.0090
-8.750 -0.9026 0.01842 0.01227 -0.0087 1.0000 0.0093
-8.500 -0.8852 0.01747 0.01122 -0.0072 1.0000 0.0098
-8.250 -0.8652 0.01683 0.01053 -0.0060 1.0000 0.0103
-8.000 -0.8449 0.01625 0.00990 -0.0049 1.0000 0.0108
-7.750 -0.8243 0.01571 0.00930 -0.0037 1.0000 0.0114
-7.500 -0.8033 0.01523 0.00876 -0.0026 1.0000 0.0123
-7.250 -0.7820 0.01480 0.00826 -0.0015 1.0000 0.0129
-7.000 -0.7632 0.01409 0.00748 0.0000 1.0000 0.0138
-6.750 -0.7425 0.01360 0.00697 0.0012 1.0000 0.0149
-6.500 -0.7214 0.01318 0.00652 0.0024 1.0000 0.0160
-6.250 -0.7002 0.01280 0.00608 0.0036 1.0000 0.0172
-6.000 -0.6791 0.01243 0.00567 0.0048 1.0000 0.0186
-5.750 -0.6470 0.01194 0.00518 0.0036 0.9959 0.0215
-5.500 -0.6152 0.01159 0.00479 0.0025 0.9904 0.0242
-5.250 -0.5828 0.01119 0.00438 0.0013 0.9845 0.0282
-5.000 -0.5512 0.01087 0.00406 0.0003 0.9778 0.0335
-4.750 -0.5175 0.01051 0.00372 -0.0012 0.9713 0.0425
-4.500 -0.4851 0.01017 0.00342 -0.0024 0.9622 0.0543
-4.250 -0.4515 0.00979 0.00312 -0.0039 0.9523 0.0751
-4.000 -0.4183 0.00939 0.00283 -0.0053 0.9398 0.1069
-3.750 -0.3875 0.00893 0.00254 -0.0062 0.9239 0.1542
-3.500 -0.3597 0.00844 0.00226 -0.0065 0.9044 0.2169
-3.000 -0.3124 0.00737 0.00176 -0.0052 0.8625 0.3937
-2.750 -0.2883 0.00709 0.00164 -0.0045 0.8435 0.4619
-2.500 -0.2631 0.00696 0.00155 -0.0039 0.8256 0.4978
-2.250 -0.2376 0.00687 0.00148 -0.0034 0.8082 0.5272
-2.000 -0.2117 0.00681 0.00140 -0.0029 0.7915 0.5517
-1.750 -0.1858 0.00675 0.00135 -0.0024 0.7762 0.5739
-1.500 -0.1595 0.00671 0.00131 -0.0020 0.7622 0.5941
-1.250 -0.1333 0.00666 0.00127 -0.0016 0.7488 0.6128
-1.000 -0.1069 0.00663 0.00124 -0.0012 0.7358 0.6304
-0.750 -0.0804 0.00661 0.00121 -0.0009 0.7229 0.6466
-0.500 -0.0537 0.00659 0.00120 -0.0005 0.7105 0.6613
-0.250 -0.0269 0.00658 0.00119 -0.0003 0.6989 0.6745
0.000 0.0000 0.00657 0.00119 0.0000 0.6870 0.6870
0.250 0.0269 0.00658 0.00119 0.0003 0.6745 0.6989
0.500 0.0537 0.00659 0.00120 0.0005 0.6613 0.7105
0.750 0.0804 0.00661 0.00121 0.0009 0.6465 0.7228
1.000 0.1069 0.00663 0.00124 0.0012 0.6305 0.7357
1.250 0.1333 0.00666 0.00127 0.0016 0.6128 0.7489
1.500 0.1595 0.00671 0.00131 0.0020 0.5941 0.7622
1.750 0.1858 0.00675 0.00135 0.0024 0.5739 0.7762
2.000 0.2117 0.00681 0.00140 0.0029 0.5513 0.7915
2.250 0.2376 0.00687 0.00148 0.0034 0.5268 0.8082
2.500 0.2632 0.00696 0.00155 0.0039 0.4984 0.8256
2.750 0.2884 0.00709 0.00164 0.0045 0.4613 0.8435
3.000 0.3126 0.00736 0.00176 0.0052 0.3958 0.8625
3.250 0.3351 0.00791 0.00199 0.0061 0.2984 0.8835
3.500 0.3598 0.00844 0.00226 0.0064 0.2174 0.9044
3.750 0.3876 0.00893 0.00254 0.0062 0.1539 0.9239
4.000 0.4183 0.00940 0.00283 0.0053 0.1058 0.9399
4.250 0.4515 0.00980 0.00312 0.0039 0.0749 0.9523
4.500 0.4853 0.01017 0.00342 0.0024 0.0543 0.9625
4.750 0.5176 0.01051 0.00372 0.0012 0.0425 0.9714
5.000 0.5513 0.01087 0.00406 -0.0003 0.0335 0.9781
5.250 0.5831 0.01119 0.00438 -0.0013 0.0282 0.9848
5.500 0.6155 0.01159 0.00479 -0.0025 0.0242 0.9905
5.750 0.6472 0.01195 0.00519 -0.0036 0.0215 0.9961
6.000 0.6786 0.01242 0.00567 -0.0047 0.0186 1.0000
6.250 0.6997 0.01280 0.00608 -0.0035 0.0172 1.0000
6.500 0.7210 0.01318 0.00651 -0.0023 0.0160 1.0000
6.750 0.7422 0.01359 0.00696 -0.0012 0.0148 1.0000
7.000 0.7628 0.01409 0.00748 0.0001 0.0138 1.0000
7.250 0.7818 0.01479 0.00825 0.0015 0.0129 1.0000
7.500 0.8031 0.01524 0.00876 0.0026 0.0123 1.0000
7.750 0.8241 0.01573 0.00932 0.0038 0.0115 1.0000
8.000 0.8449 0.01626 0.00990 0.0049 0.0108 1.0000
8.250 0.8654 0.01683 0.01053 0.0060 0.0103 1.0000
8.500 0.8853 0.01748 0.01123 0.0072 0.0099 1.0000
8.750 0.9032 0.01839 0.01223 0.0086 0.0093 1.0000
9.000 0.9209 0.01937 0.01332 0.0100 0.0091 1.0000
9.250 0.9398 0.02020 0.01427 0.0113 0.0088 1.0000
9.500 0.9581 0.02110 0.01531 0.0125 0.0085 1.0000
9.750 0.9748 0.02222 0.01658 0.0140 0.0083 1.0000
10.000 0.9910 0.02334 0.01786 0.0154 0.0080 1.0000
10.250 1.0064 0.02451 0.01918 0.0169 0.0078 1.0000
10.500 1.0207 0.02572 0.02057 0.0185 0.0075 1.0000
10.750 1.0352 0.02672 0.02169 0.0199 0.0072 1.0000
11.000 1.0475 0.02787 0.02297 0.0216 0.0070 1.0000
11.250 1.0613 0.02864 0.02380 0.0230 0.0068 1.0000
11.500 1.0670 0.03003 0.02534 0.0254 0.0067 1.0000
11.750 1.0660 0.03165 0.02710 0.0284 0.0065 1.0000
12.000 1.0597 0.03387 0.02952 0.0313 0.0064 1.0000
12.250 1.0533 0.03627 0.03211 0.0333 0.0063 1.0000
12.500 1.0469 0.03891 0.03496 0.0345 0.0062 1.0000
12.750 1.0393 0.04195 0.03819 0.0348 0.0062 1.0000
13.000 1.0261 0.04604 0.04251 0.0341 0.0061 1.0000
13.250 1.0099 0.05100 0.04766 0.0321 0.0062 1.0000
13.500 0.9920 0.05696 0.05383 0.0288 0.0061 1.0000
13.750 0.9727 0.06386 0.06092 0.0244 0.0061 1.0000
14.000 0.9429 0.07389 0.07113 0.0175 0.0062 1.0000
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Polar data table (+)
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