AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 49.56 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-200000-n5.txt Download as CSV file: xf-ag47ct02r-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6379 0.12170 0.11818 0.0327 1.0000 0.0175
-9.250 -0.6335 0.11781 0.11431 0.0305 1.0000 0.0176
-9.000 -0.6357 0.11195 0.10849 0.0308 1.0000 0.0184
-8.750 -0.6285 0.10883 0.10538 0.0315 1.0000 0.0194
-8.500 -0.6241 0.10522 0.10176 0.0301 1.0000 0.0199
-8.250 -0.6201 0.10147 0.09803 0.0283 1.0000 0.0203
-8.000 -0.6162 0.09767 0.09426 0.0263 1.0000 0.0206
-7.750 -0.6123 0.09381 0.09044 0.0239 1.0000 0.0209
-7.500 -0.6082 0.08984 0.08649 0.0210 1.0000 0.0213
-7.250 -0.6008 0.08544 0.08211 0.0167 1.0000 0.0216
-7.000 -0.5903 0.08062 0.07730 0.0114 1.0000 0.0219
-6.750 -0.5771 0.07550 0.07216 0.0056 1.0000 0.0221
-6.500 -0.5615 0.07008 0.06671 -0.0003 1.0000 0.0221
-6.250 -0.5358 0.06113 0.05757 -0.0098 1.0000 0.0168
-6.000 -0.5210 0.05622 0.05257 -0.0128 1.0000 0.0153
-5.750 -0.4996 0.05005 0.04620 -0.0170 1.0000 0.0139
-5.250 -0.4467 0.03476 0.03000 -0.0228 1.0000 0.0111
-5.000 -0.4228 0.02993 0.02470 -0.0239 1.0000 0.0109
-4.750 -0.3973 0.02573 0.01996 -0.0243 1.0000 0.0109
-4.500 -0.3708 0.02238 0.01603 -0.0243 1.0000 0.0110
-4.250 -0.3438 0.01993 0.01307 -0.0241 1.0000 0.0112
-4.000 -0.3175 0.01736 0.01012 -0.0238 1.0000 0.0119
-3.750 -0.2911 0.01658 0.00923 -0.0237 1.0000 0.0139
-3.500 -0.2641 0.01559 0.00805 -0.0234 1.0000 0.0159
-3.250 -0.2371 0.01430 0.00658 -0.0229 1.0000 0.0168
-3.000 -0.2103 0.01320 0.00537 -0.0224 1.0000 0.0179
-2.750 -0.1837 0.01217 0.00430 -0.0221 1.0000 0.0207
-2.500 -0.1567 0.01172 0.00377 -0.0218 1.0000 0.0265
-2.250 -0.1297 0.01103 0.00307 -0.0216 1.0000 0.0360
-2.000 -0.1027 0.01050 0.00263 -0.0213 1.0000 0.0583
-1.750 -0.0759 0.00997 0.00233 -0.0212 1.0000 0.1113
-1.500 -0.0495 0.00936 0.00212 -0.0212 1.0000 0.2140
-1.250 -0.0239 0.00852 0.00197 -0.0212 1.0000 0.4015
-1.000 -0.0029 0.00740 0.00193 -0.0198 1.0000 0.6882
-0.750 0.0283 0.00672 0.00184 -0.0193 1.0000 1.0000
-0.500 0.0554 0.00673 0.00176 -0.0191 0.9986 1.0000
-0.250 0.0972 0.00677 0.00167 -0.0220 0.9544 1.0000
0.000 0.1384 0.00684 0.00158 -0.0245 0.8794 1.0000
0.250 0.1671 0.00703 0.00148 -0.0239 0.8032 1.0000
0.500 0.1919 0.00727 0.00144 -0.0228 0.7545 1.0000
0.750 0.2174 0.00751 0.00145 -0.0220 0.7216 1.0000
1.000 0.2435 0.00773 0.00150 -0.0214 0.6949 1.0000
1.250 0.2702 0.00788 0.00155 -0.0209 0.6643 1.0000
1.500 0.2966 0.00805 0.00160 -0.0204 0.6283 1.0000
1.750 0.3228 0.00825 0.00164 -0.0199 0.5861 1.0000
2.000 0.3489 0.00849 0.00168 -0.0194 0.5376 1.0000
2.250 0.3750 0.00879 0.00175 -0.0189 0.4845 1.0000
2.500 0.4011 0.00913 0.00186 -0.0186 0.4282 1.0000
2.750 0.4273 0.00951 0.00204 -0.0183 0.3705 1.0000
3.000 0.4535 0.00992 0.00222 -0.0180 0.3145 1.0000
3.250 0.4797 0.01036 0.00245 -0.0178 0.2638 1.0000
3.500 0.5061 0.01079 0.00270 -0.0177 0.2199 1.0000
3.750 0.5325 0.01122 0.00299 -0.0175 0.1833 1.0000
4.000 0.5590 0.01165 0.00335 -0.0174 0.1548 1.0000
4.250 0.5855 0.01209 0.00371 -0.0172 0.1291 1.0000
4.500 0.6120 0.01251 0.00410 -0.0170 0.1102 1.0000
4.750 0.6384 0.01296 0.00453 -0.0168 0.0947 1.0000
5.000 0.6646 0.01343 0.00503 -0.0166 0.0806 1.0000
5.250 0.6908 0.01394 0.00556 -0.0164 0.0703 1.0000
5.500 0.7168 0.01451 0.00614 -0.0162 0.0608 1.0000
5.750 0.7427 0.01505 0.00672 -0.0159 0.0519 1.0000
6.000 0.7684 0.01570 0.00748 -0.0156 0.0458 1.0000
6.250 0.7937 0.01642 0.00826 -0.0153 0.0392 1.0000
6.500 0.8191 0.01713 0.00911 -0.0150 0.0344 1.0000
6.750 0.8441 0.01794 0.01003 -0.0146 0.0305 1.0000
7.000 0.8677 0.01920 0.01138 -0.0142 0.0272 1.0000
7.250 0.8926 0.02003 0.01241 -0.0138 0.0242 1.0000
7.500 0.9167 0.02107 0.01365 -0.0134 0.0219 1.0000
7.750 0.9398 0.02235 0.01508 -0.0129 0.0201 1.0000
8.000 0.9601 0.02469 0.01765 -0.0123 0.0187 1.0000
8.250 0.9823 0.02639 0.01969 -0.0117 0.0177 1.0000
8.500 1.0038 0.02806 0.02171 -0.0112 0.0160 1.0000
8.750 1.0238 0.03003 0.02401 -0.0107 0.0148 1.0000
9.000 1.0418 0.03232 0.02664 -0.0103 0.0140 1.0000
9.250 1.0579 0.03479 0.02941 -0.0099 0.0133 1.0000
9.500 1.0695 0.03805 0.03304 -0.0096 0.0127 1.0000
9.750 1.0703 0.04328 0.03879 -0.0097 0.0123 1.0000
10.000 1.0663 0.04867 0.04470 -0.0104 0.0120 1.0000
10.250 1.0561 0.05435 0.05079 -0.0125 0.0119 1.0000
10.500 1.0366 0.06108 0.05772 -0.0178 0.0120 1.0000
10.750 0.9384 0.09789 0.09479 -0.0463 0.0143 1.0000
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Polar data table (+)
Polar graphs
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