AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 44.53 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-100000.txt Download as CSV file: xf-ag46ct02r-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5816 0.10928 0.10453 0.0208 1.0000 0.0701
-8.250 -0.5861 0.10670 0.10203 0.0143 1.0000 0.0715
-8.000 -0.5870 0.10330 0.09870 0.0046 1.0000 0.0719
-7.750 -0.5763 0.09746 0.09289 0.0119 1.0000 0.0738
-7.500 -0.5652 0.09377 0.08917 0.0137 1.0000 0.0766
-7.250 -0.5586 0.09007 0.08551 0.0111 1.0000 0.0798
-7.000 -0.5497 0.08549 0.08093 0.0001 1.0000 0.0844
-6.750 -0.5391 0.07969 0.07508 -0.0087 1.0000 0.0865
-6.500 -0.5291 0.07641 0.07188 -0.0036 1.0000 0.0895
-6.250 -0.5143 0.07237 0.06781 -0.0074 1.0000 0.0958
-6.000 -0.4985 0.06702 0.06237 -0.0138 1.0000 0.1017
-5.750 -0.4771 0.06283 0.05788 -0.0213 1.0000 0.1136
-5.500 -0.4660 0.05968 0.05498 -0.0166 1.0000 0.1200
-5.250 -0.4466 0.05549 0.05068 -0.0197 1.0000 0.1315
-5.000 -0.4258 0.05158 0.04665 -0.0222 1.0000 0.1445
-4.750 -0.4050 0.04807 0.04305 -0.0236 1.0000 0.1589
-4.500 -0.3835 0.04482 0.03968 -0.0244 1.0000 0.1751
-4.250 -0.3610 0.04168 0.03640 -0.0257 1.0000 0.1995
-4.000 -0.3011 0.02897 0.02168 -0.0315 1.0000 0.0665
-3.750 -0.2698 0.02555 0.01736 -0.0309 1.0000 0.0579
-3.500 -0.2421 0.02281 0.01423 -0.0305 1.0000 0.0572
-3.250 -0.2148 0.02056 0.01166 -0.0301 1.0000 0.0614
-3.000 -0.1874 0.01881 0.00978 -0.0294 1.0000 0.0656
-2.750 -0.1595 0.01729 0.00804 -0.0286 1.0000 0.0712
-2.500 -0.1334 0.01578 0.00661 -0.0280 1.0000 0.0876
-2.250 -0.1075 0.01435 0.00543 -0.0273 1.0000 0.1227
-2.000 -0.0857 0.01138 0.00437 -0.0266 1.0000 0.4698
-1.750 -0.0536 0.00981 0.00399 -0.0249 1.0000 1.0000
-1.500 -0.0277 0.00979 0.00365 -0.0245 1.0000 1.0000
-1.250 -0.0021 0.00977 0.00338 -0.0241 1.0000 1.0000
-1.000 0.0234 0.00978 0.00320 -0.0237 1.0000 1.0000
-0.750 0.0487 0.00980 0.00308 -0.0233 1.0000 1.0000
-0.500 0.0738 0.00984 0.00301 -0.0230 1.0000 1.0000
-0.250 0.0987 0.00992 0.00299 -0.0227 1.0000 1.0000
0.000 0.1230 0.01004 0.00307 -0.0226 1.0000 1.0000
0.250 0.1458 0.01027 0.00327 -0.0226 1.0000 1.0000
0.500 0.1826 0.01058 0.00355 -0.0257 0.9897 1.0000
0.750 0.2442 0.01069 0.00364 -0.0327 0.9602 1.0000
1.000 0.2953 0.01073 0.00366 -0.0371 0.9249 1.0000
1.250 0.3344 0.01078 0.00365 -0.0385 0.8855 1.0000
1.500 0.3629 0.01092 0.00370 -0.0377 0.8456 1.0000
1.750 0.3878 0.01114 0.00379 -0.0361 0.8083 1.0000
2.000 0.4118 0.01142 0.00392 -0.0344 0.7743 1.0000
2.250 0.4357 0.01176 0.00412 -0.0329 0.7409 1.0000
2.500 0.4596 0.01215 0.00440 -0.0315 0.7092 1.0000
2.750 0.4839 0.01251 0.00467 -0.0303 0.6768 1.0000
3.000 0.5085 0.01276 0.00487 -0.0291 0.6431 1.0000
3.250 0.5331 0.01299 0.00501 -0.0279 0.6100 1.0000
3.500 0.5578 0.01322 0.00517 -0.0268 0.5732 1.0000
3.750 0.5824 0.01351 0.00540 -0.0258 0.5346 1.0000
4.000 0.6071 0.01384 0.00562 -0.0248 0.4927 1.0000
4.250 0.6317 0.01422 0.00587 -0.0238 0.4469 1.0000
4.500 0.6559 0.01473 0.00618 -0.0229 0.3999 1.0000
4.750 0.6803 0.01535 0.00668 -0.0222 0.3500 1.0000
5.000 0.7044 0.01611 0.00722 -0.0215 0.3045 1.0000
5.250 0.7288 0.01697 0.00791 -0.0209 0.2644 1.0000
5.500 0.7530 0.01790 0.00869 -0.0204 0.2305 1.0000
5.750 0.7775 0.01892 0.00963 -0.0199 0.2021 1.0000
6.000 0.8017 0.01998 0.01063 -0.0193 0.1771 1.0000
6.250 0.8263 0.02115 0.01185 -0.0188 0.1554 1.0000
6.500 0.8502 0.02246 0.01310 -0.0183 0.1360 1.0000
6.750 0.8745 0.02394 0.01473 -0.0176 0.1194 1.0000
7.000 0.8981 0.02538 0.01630 -0.0170 0.1038 1.0000
7.250 0.9217 0.02736 0.01848 -0.0163 0.0921 1.0000
7.500 0.9443 0.02937 0.02066 -0.0157 0.0815 1.0000
7.750 0.9665 0.03152 0.02288 -0.0151 0.0729 1.0000
8.000 0.9862 0.03481 0.02689 -0.0140 0.0674 1.0000
8.250 1.0061 0.03702 0.02907 -0.0136 0.0603 1.0000
8.500 1.0195 0.04147 0.03430 -0.0126 0.0581 1.0000
8.750 1.0282 0.04661 0.04018 -0.0117 0.0569 1.0000
9.000 1.0306 0.05231 0.04652 -0.0114 0.0563 1.0000
9.250 1.0265 0.05831 0.05304 -0.0117 0.0559 1.0000
9.500 1.0161 0.06456 0.05967 -0.0128 0.0562 1.0000
9.750 1.0009 0.07083 0.06618 -0.0148 0.0570 1.0000
10.000 0.9833 0.07670 0.07218 -0.0174 0.0580 1.0000
10.250 0.9680 0.08328 0.07881 -0.0217 0.0588 1.0000
10.500 0.9572 0.09014 0.08568 -0.0254 0.0595 1.0000
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Polar data table (+)
Polar graphs
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