AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 66.7 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-500000-n5.txt Download as CSV file: xf-ag47ct02r-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG47ct -02f rot.
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 -0.6347 0.10162 0.09942 0.0315 1.0000 0.0067
-8.250 -0.6320 0.09768 0.09550 0.0296 1.0000 0.0065
-8.000 -0.6295 0.09346 0.09130 0.0271 1.0000 0.0064
-7.750 -0.6269 0.08915 0.08701 0.0242 1.0000 0.0064
-7.500 -0.6218 0.08441 0.08230 0.0197 1.0000 0.0064
-7.250 -0.6118 0.07900 0.07688 0.0135 1.0000 0.0064
-7.000 -0.5984 0.07296 0.07081 0.0063 1.0000 0.0065
-5.750 -0.4957 0.04077 0.03793 -0.0206 1.0000 0.0067
-5.500 -0.4722 0.03441 0.03123 -0.0229 1.0000 0.0065
-5.250 -0.4478 0.02777 0.02412 -0.0242 1.0000 0.0062
-5.000 -0.4227 0.02096 0.01659 -0.0246 1.0000 0.0059
-4.750 -0.3966 0.01678 0.01175 -0.0243 1.0000 0.0058
-4.500 -0.3700 0.01448 0.00903 -0.0239 1.0000 0.0059
-4.250 -0.3432 0.01295 0.00721 -0.0236 1.0000 0.0062
-4.000 -0.3164 0.01184 0.00591 -0.0232 1.0000 0.0066
-3.750 -0.2894 0.01108 0.00499 -0.0229 1.0000 0.0070
-3.500 -0.2626 0.01015 0.00397 -0.0226 1.0000 0.0078
-3.250 -0.2356 0.00968 0.00347 -0.0224 1.0000 0.0086
-3.000 -0.2085 0.00939 0.00316 -0.0221 1.0000 0.0101
-2.750 -0.1813 0.00906 0.00281 -0.0219 1.0000 0.0113
-2.500 -0.1541 0.00851 0.00220 -0.0216 1.0000 0.0142
-2.250 -0.1269 0.00824 0.00190 -0.0213 1.0000 0.0179
-2.000 -0.0993 0.00795 0.00165 -0.0212 0.9990 0.0285
-1.750 -0.0623 0.00764 0.00145 -0.0232 0.9712 0.0545
-1.500 -0.0246 0.00738 0.00126 -0.0252 0.9029 0.0975
-1.250 -0.0018 0.00741 0.00112 -0.0237 0.7987 0.1508
-1.000 0.0232 0.00729 0.00103 -0.0230 0.7462 0.2362
-0.500 0.0753 0.00651 0.00093 -0.0226 0.7020 0.5315
-0.250 0.1004 0.00600 0.00093 -0.0221 0.6834 0.6996
0.000 0.1204 0.00549 0.00094 -0.0198 0.6626 0.8734
0.250 0.1557 0.00541 0.00088 -0.0210 0.6330 1.0000
0.500 0.1829 0.00554 0.00084 -0.0207 0.6001 1.0000
0.750 0.2100 0.00570 0.00082 -0.0205 0.5615 1.0000
1.000 0.2371 0.00589 0.00082 -0.0202 0.5190 1.0000
1.250 0.2642 0.00612 0.00085 -0.0200 0.4732 1.0000
1.500 0.2913 0.00636 0.00089 -0.0199 0.4263 1.0000
1.750 0.3184 0.00662 0.00096 -0.0197 0.3786 1.0000
2.000 0.3456 0.00689 0.00104 -0.0196 0.3338 1.0000
2.250 0.3727 0.00718 0.00115 -0.0195 0.2872 1.0000
2.500 0.3998 0.00746 0.00127 -0.0194 0.2484 1.0000
3.000 0.4541 0.00803 0.00157 -0.0192 0.1821 1.0000
3.500 0.5084 0.00859 0.00192 -0.0190 0.1308 1.0000
3.750 0.5356 0.00885 0.00212 -0.0189 0.1137 1.0000
4.000 0.5627 0.00912 0.00235 -0.0188 0.0979 1.0000
4.250 0.5898 0.00940 0.00259 -0.0186 0.0835 1.0000
4.500 0.6168 0.00968 0.00284 -0.0185 0.0729 1.0000
4.750 0.6437 0.00999 0.00312 -0.0183 0.0621 1.0000
5.000 0.6707 0.01027 0.00342 -0.0182 0.0539 1.0000
5.250 0.6976 0.01058 0.00374 -0.0180 0.0472 1.0000
5.500 0.7242 0.01095 0.00408 -0.0179 0.0395 1.0000
5.750 0.7510 0.01126 0.00445 -0.0177 0.0349 1.0000
6.000 0.7775 0.01167 0.00488 -0.0175 0.0294 1.0000
6.250 0.8039 0.01206 0.00532 -0.0173 0.0256 1.0000
6.500 0.8302 0.01248 0.00576 -0.0171 0.0219 1.0000
6.750 0.8561 0.01308 0.00641 -0.0168 0.0186 1.0000
7.000 0.8822 0.01354 0.00697 -0.0166 0.0172 1.0000
7.250 0.9080 0.01407 0.00759 -0.0163 0.0156 1.0000
7.500 0.9334 0.01466 0.00826 -0.0161 0.0138 1.0000
7.750 0.9577 0.01562 0.00933 -0.0157 0.0120 1.0000
8.000 0.9829 0.01626 0.01010 -0.0154 0.0114 1.0000
8.250 1.0075 0.01703 0.01101 -0.0150 0.0107 1.0000
8.500 1.0318 0.01786 0.01198 -0.0147 0.0099 1.0000
8.750 1.0561 0.01858 0.01281 -0.0144 0.0091 1.0000
9.000 1.0798 0.01941 0.01373 -0.0141 0.0083 1.0000
9.250 1.1006 0.02104 0.01560 -0.0135 0.0075 1.0000
9.500 1.1232 0.02211 0.01686 -0.0131 0.0072 1.0000
9.750 1.1448 0.02339 0.01836 -0.0127 0.0068 1.0000
10.000 1.1653 0.02484 0.02004 -0.0122 0.0064 1.0000
10.250 1.1854 0.02625 0.02166 -0.0118 0.0059 1.0000
10.500 1.2058 0.02743 0.02299 -0.0114 0.0055 1.0000
10.750 1.2260 0.02853 0.02423 -0.0111 0.0051 1.0000
11.000 1.2411 0.03058 0.02648 -0.0108 0.0047 1.0000
11.250 1.2516 0.03334 0.02955 -0.0103 0.0045 1.0000
11.500 1.2618 0.03592 0.03246 -0.0099 0.0043 1.0000
11.750 1.2662 0.03914 0.03600 -0.0097 0.0042 1.0000
12.000 1.2630 0.04311 0.04028 -0.0101 0.0041 1.0000
12.250 1.2473 0.04812 0.04555 -0.0121 0.0040 1.0000
12.500 1.2236 0.05872 0.05642 -0.0235 0.0041 1.0000
12.750 1.1835 0.07566 0.07351 -0.0370 0.0044 1.0000
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Polar data table (+)
Polar graphs
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