AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 44.37 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-100000-n5.txt Download as CSV file: xf-ag46ct02r-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5703 0.09893 0.09419 0.0169 1.0000 0.0423
-7.750 -0.5669 0.09500 0.09031 0.0142 1.0000 0.0427
-7.500 -0.5635 0.09074 0.08611 0.0075 1.0000 0.0446
-7.000 -0.4751 0.06430 0.05986 -0.0087 1.0000 0.0229
-6.750 -0.5300 0.07092 0.06618 -0.0096 1.0000 0.0226
-6.500 -0.5182 0.06625 0.06148 -0.0124 1.0000 0.0219
-6.250 -0.5029 0.06103 0.05613 -0.0163 1.0000 0.0213
-6.000 -0.4845 0.05540 0.05032 -0.0204 1.0000 0.0212
-5.750 -0.4636 0.04959 0.04425 -0.0241 1.0000 0.0215
-5.500 -0.4410 0.04412 0.03841 -0.0268 1.0000 0.0221
-5.250 -0.4176 0.03929 0.03313 -0.0284 1.0000 0.0225
-5.000 -0.3941 0.03497 0.02835 -0.0295 1.0000 0.0224
-4.750 -0.3694 0.03110 0.02398 -0.0300 1.0000 0.0223
-4.500 -0.3436 0.02778 0.02011 -0.0301 1.0000 0.0224
-4.250 -0.3170 0.02503 0.01683 -0.0299 1.0000 0.0227
-4.000 -0.2900 0.02281 0.01415 -0.0296 1.0000 0.0231
-3.750 -0.2637 0.02044 0.01147 -0.0292 1.0000 0.0241
-3.500 -0.2378 0.01912 0.01007 -0.0289 1.0000 0.0275
-3.250 -0.2112 0.01795 0.00872 -0.0284 1.0000 0.0314
-3.000 -0.1848 0.01669 0.00733 -0.0278 1.0000 0.0341
-2.750 -0.1589 0.01561 0.00626 -0.0274 1.0000 0.0417
-2.500 -0.1326 0.01469 0.00531 -0.0270 1.0000 0.0535
-2.250 -0.1063 0.01381 0.00452 -0.0266 1.0000 0.0857
-2.000 -0.0808 0.01279 0.00403 -0.0264 1.0000 0.1869
-1.500 -0.0390 0.01032 0.00369 -0.0235 1.0000 0.7242
-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 0.0817 0.00985 0.00299 -0.0246 0.9878 1.0000
-0.250 0.1245 0.00991 0.00289 -0.0277 0.9504 1.0000
0.000 0.1657 0.00998 0.00281 -0.0302 0.9038 1.0000
0.250 0.2027 0.01008 0.00272 -0.0316 0.8532 1.0000
0.500 0.2330 0.01023 0.00265 -0.0315 0.8074 1.0000
0.750 0.2599 0.01044 0.00263 -0.0307 0.7704 1.0000
1.000 0.2861 0.01066 0.00266 -0.0299 0.7397 1.0000
1.250 0.3123 0.01091 0.00273 -0.0292 0.7135 1.0000
1.500 0.3386 0.01114 0.00286 -0.0286 0.6880 1.0000
1.750 0.3650 0.01135 0.00298 -0.0281 0.6612 1.0000
2.000 0.3913 0.01154 0.00309 -0.0275 0.6338 1.0000
2.250 0.4175 0.01174 0.00320 -0.0269 0.6056 1.0000
2.500 0.4436 0.01195 0.00332 -0.0263 0.5761 1.0000
2.750 0.4697 0.01219 0.00349 -0.0258 0.5454 1.0000
3.000 0.4957 0.01244 0.00364 -0.0252 0.5134 1.0000
3.250 0.5217 0.01272 0.00383 -0.0247 0.4796 1.0000
3.500 0.5476 0.01303 0.00404 -0.0242 0.4441 1.0000
3.750 0.5734 0.01337 0.00433 -0.0237 0.4071 1.0000
4.000 0.5991 0.01377 0.00462 -0.0233 0.3698 1.0000
4.250 0.6247 0.01421 0.00496 -0.0229 0.3317 1.0000
4.500 0.6503 0.01469 0.00535 -0.0225 0.2948 1.0000
4.750 0.6756 0.01523 0.00583 -0.0222 0.2593 1.0000
5.000 0.7010 0.01580 0.00634 -0.0219 0.2268 1.0000
5.250 0.7262 0.01642 0.00690 -0.0216 0.1980 1.0000
5.500 0.7512 0.01708 0.00753 -0.0213 0.1731 1.0000
5.750 0.7760 0.01780 0.00822 -0.0209 0.1517 1.0000
6.000 0.8009 0.01852 0.00902 -0.0206 0.1325 1.0000
6.250 0.8254 0.01930 0.00984 -0.0202 0.1153 1.0000
6.500 0.8496 0.02016 0.01075 -0.0198 0.1008 1.0000
6.750 0.8735 0.02106 0.01170 -0.0195 0.0867 1.0000
7.000 0.8971 0.02208 0.01283 -0.0190 0.0754 1.0000
7.250 0.9203 0.02312 0.01403 -0.0185 0.0642 1.0000
7.500 0.9425 0.02445 0.01548 -0.0179 0.0563 1.0000
7.750 0.9643 0.02573 0.01684 -0.0175 0.0485 1.0000
8.000 0.9861 0.02723 0.01861 -0.0167 0.0422 1.0000
8.250 1.0062 0.02888 0.02037 -0.0161 0.0378 1.0000
8.500 1.0262 0.03081 0.02262 -0.0154 0.0333 1.0000
8.750 1.0452 0.03274 0.02482 -0.0147 0.0299 1.0000
9.000 1.0620 0.03501 0.02732 -0.0140 0.0278 1.0000
9.250 1.0756 0.03820 0.03087 -0.0131 0.0260 1.0000
9.500 1.0882 0.04119 0.03439 -0.0124 0.0238 1.0000
9.750 1.0971 0.04436 0.03801 -0.0118 0.0220 1.0000
10.000 1.1010 0.04812 0.04217 -0.0113 0.0211 1.0000
10.250 1.0995 0.05214 0.04657 -0.0110 0.0206 1.0000
10.500 1.0913 0.05647 0.05123 -0.0113 0.0202 1.0000
10.750 1.0748 0.06138 0.05641 -0.0127 0.0202 1.0000
11.000 1.0523 0.06866 0.06396 -0.0184 0.0205 1.0000
11.250 1.0215 0.07978 0.07531 -0.0282 0.0213 1.0000
11.500 0.9780 0.09646 0.09208 -0.0409 0.0231 1.0000
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Polar data table (+)
Polar graphs
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