AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 55.67 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-200000-n5.txt Download as CSV file: xf-ag46ct02r-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5940 0.11516 0.11165 0.0281 1.0000 0.0210
-9.000 -0.5902 0.11133 0.10784 0.0258 1.0000 0.0216
-8.750 -0.5870 0.10748 0.10402 0.0225 1.0000 0.0223
-8.500 -0.5829 0.10362 0.10020 0.0190 1.0000 0.0227
-8.250 -0.5787 0.09966 0.09627 0.0160 1.0000 0.0229
-8.000 -0.5741 0.09565 0.09229 0.0131 1.0000 0.0230
-7.750 -0.5691 0.09144 0.08812 0.0097 1.0000 0.0230
-7.500 -0.5606 0.08669 0.08339 0.0047 1.0000 0.0231
-7.250 -0.5496 0.08157 0.07825 -0.0007 1.0000 0.0231
-6.750 -0.5354 0.06838 0.06501 -0.0082 1.0000 0.0147
-6.500 -0.5226 0.06345 0.06004 -0.0121 1.0000 0.0139
-6.250 -0.5056 0.05768 0.05413 -0.0170 1.0000 0.0131
-6.000 -0.4860 0.05123 0.04750 -0.0217 1.0000 0.0124
-5.750 -0.4640 0.04351 0.03946 -0.0260 1.0000 0.0115
-5.500 -0.4399 0.03290 0.02812 -0.0290 1.0000 0.0103
-5.250 -0.4162 0.02817 0.02279 -0.0297 1.0000 0.0103
-5.000 -0.3918 0.02461 0.01872 -0.0300 1.0000 0.0105
-4.750 -0.3665 0.02206 0.01576 -0.0300 1.0000 0.0109
-4.500 -0.3406 0.02035 0.01374 -0.0298 1.0000 0.0117
-4.250 -0.3143 0.01924 0.01241 -0.0296 1.0000 0.0135
-4.000 -0.2874 0.01768 0.01051 -0.0291 1.0000 0.0145
-3.750 -0.2607 0.01616 0.00873 -0.0286 1.0000 0.0149
-3.500 -0.2341 0.01493 0.00731 -0.0281 1.0000 0.0154
-3.250 -0.2082 0.01350 0.00580 -0.0277 1.0000 0.0167
-3.000 -0.1818 0.01273 0.00499 -0.0273 1.0000 0.0187
-2.750 -0.1552 0.01222 0.00442 -0.0270 1.0000 0.0227
-2.500 -0.1285 0.01151 0.00369 -0.0267 1.0000 0.0290
-2.250 -0.1018 0.01097 0.00315 -0.0263 1.0000 0.0433
-2.000 -0.0753 0.01041 0.00278 -0.0261 1.0000 0.0847
-1.750 -0.0491 0.00984 0.00256 -0.0261 1.0000 0.1674
-1.500 -0.0134 0.00917 0.00239 -0.0282 0.9814 0.3005
-1.250 0.0215 0.00820 0.00225 -0.0301 0.9463 0.5330
-1.000 0.0492 0.00730 0.00223 -0.0290 0.8935 0.8061
-0.750 0.0937 0.00708 0.00199 -0.0312 0.8281 1.0000
-0.500 0.1196 0.00727 0.00184 -0.0303 0.7769 1.0000
-0.250 0.1452 0.00746 0.00176 -0.0295 0.7437 1.0000
0.000 0.1714 0.00765 0.00171 -0.0289 0.7194 1.0000
0.250 0.1980 0.00782 0.00170 -0.0284 0.6994 1.0000
0.500 0.2249 0.00796 0.00170 -0.0281 0.6779 1.0000
0.750 0.2519 0.00808 0.00170 -0.0277 0.6551 1.0000
1.000 0.2788 0.00821 0.00170 -0.0274 0.6316 1.0000
1.250 0.3057 0.00835 0.00172 -0.0270 0.6069 1.0000
1.750 0.3593 0.00867 0.00179 -0.0263 0.5543 1.0000
2.000 0.3861 0.00886 0.00185 -0.0260 0.5266 1.0000
2.250 0.4130 0.00905 0.00192 -0.0257 0.4980 1.0000
2.500 0.4398 0.00926 0.00202 -0.0254 0.4677 1.0000
2.750 0.4665 0.00949 0.00215 -0.0251 0.4360 1.0000
3.000 0.4932 0.00975 0.00228 -0.0248 0.4030 1.0000
3.250 0.5199 0.01004 0.00245 -0.0246 0.3706 1.0000
3.500 0.5465 0.01034 0.00264 -0.0244 0.3374 1.0000
3.750 0.5730 0.01068 0.00289 -0.0242 0.3042 1.0000
4.000 0.5995 0.01103 0.00314 -0.0240 0.2718 1.0000
4.250 0.6259 0.01141 0.00342 -0.0238 0.2401 1.0000
4.500 0.6523 0.01181 0.00373 -0.0237 0.2116 1.0000
4.750 0.6786 0.01223 0.00411 -0.0235 0.1851 1.0000
5.000 0.7047 0.01268 0.00449 -0.0233 0.1621 1.0000
5.250 0.7309 0.01313 0.00490 -0.0231 0.1417 1.0000
5.500 0.7569 0.01361 0.00535 -0.0230 0.1238 1.0000
5.750 0.7829 0.01409 0.00587 -0.0227 0.1089 1.0000
6.000 0.8087 0.01459 0.00638 -0.0225 0.0943 1.0000
6.250 0.8344 0.01513 0.00695 -0.0223 0.0819 1.0000
6.500 0.8598 0.01571 0.00755 -0.0220 0.0701 1.0000
6.750 0.8849 0.01635 0.00821 -0.0218 0.0593 1.0000
7.000 0.9100 0.01698 0.00895 -0.0215 0.0502 1.0000
7.250 0.9348 0.01769 0.00975 -0.0211 0.0421 1.0000
7.500 0.9585 0.01861 0.01072 -0.0207 0.0358 1.0000
7.750 0.9828 0.01937 0.01161 -0.0204 0.0301 1.0000
8.000 1.0053 0.02055 0.01287 -0.0199 0.0259 1.0000
8.250 1.0283 0.02158 0.01411 -0.0193 0.0228 1.0000
8.500 1.0506 0.02264 0.01527 -0.0189 0.0197 1.0000
8.750 1.0708 0.02418 0.01703 -0.0182 0.0175 1.0000
9.000 1.0912 0.02568 0.01876 -0.0175 0.0160 1.0000
9.250 1.1105 0.02731 0.02063 -0.0168 0.0147 1.0000
9.500 1.1293 0.02885 0.02235 -0.0161 0.0135 1.0000
9.750 1.1446 0.03090 0.02458 -0.0155 0.0123 1.0000
10.000 1.1594 0.03306 0.02704 -0.0147 0.0114 1.0000
10.250 1.1719 0.03552 0.02985 -0.0138 0.0107 1.0000
10.500 1.1805 0.03839 0.03308 -0.0129 0.0102 1.0000
10.750 1.1848 0.04155 0.03659 -0.0121 0.0098 1.0000
11.000 1.1839 0.04500 0.04037 -0.0115 0.0095 1.0000
11.250 1.1751 0.04865 0.04431 -0.0111 0.0094 1.0000
11.500 1.1620 0.05337 0.04930 -0.0132 0.0093 1.0000
11.750 1.1464 0.05984 0.05602 -0.0182 0.0093 1.0000
12.000 1.1279 0.06793 0.06434 -0.0249 0.0094 1.0000
12.250 1.1053 0.07772 0.07432 -0.0326 0.0096 1.0000
12.500 1.0787 0.08890 0.08565 -0.0404 0.0099 1.0000
12.750 1.0480 0.10132 0.09817 -0.0480 0.0103 1.0000
13.000 1.0131 0.11493 0.11182 -0.0553 0.0109 1.0000
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Polar data table (+)
Polar graphs
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