AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.45 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-50000.txt Download as CSV file: xf-ag455ct02r-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: AG455ct -02f rot.
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.5686 0.10905 0.10259 0.0217 1.0000 0.1916
-7.750 -0.5547 0.10413 0.09770 0.0227 1.0000 0.1993
-7.500 -0.5697 0.10311 0.09682 0.0166 1.0000 0.2066
-7.250 -0.5516 0.09791 0.09163 0.0197 1.0000 0.2186
-7.000 -0.5424 0.09385 0.08762 0.0198 1.0000 0.2284
-6.750 -0.5368 0.09026 0.08409 0.0184 1.0000 0.2407
-6.500 -0.5293 0.08673 0.08062 0.0176 1.0000 0.2567
-6.250 -0.5280 0.08394 0.07789 0.0129 1.0000 0.2767
-6.000 -0.5133 0.07970 0.07371 0.0170 1.0000 0.2972
-5.750 -0.5058 0.07636 0.07043 0.0166 1.0000 0.3228
-5.500 -0.4961 0.07300 0.06713 0.0179 1.0000 0.3510
-5.250 -0.4849 0.06961 0.06380 0.0201 1.0000 0.3808
-5.000 -0.4775 0.06671 0.06093 0.0218 1.0000 0.4200
-4.750 -0.4637 0.06334 0.05762 0.0265 1.0000 0.4567
-4.500 -0.3879 0.04973 0.04295 -0.0217 1.0000 0.2360
-4.250 -0.3290 0.03904 0.03053 -0.0326 1.0000 0.1221
-4.000 -0.3019 0.03501 0.02619 -0.0331 1.0000 0.1156
-3.750 -0.2723 0.03159 0.02217 -0.0335 1.0000 0.1141
-3.500 -0.2433 0.02892 0.01901 -0.0335 1.0000 0.1190
-3.250 -0.2131 0.02634 0.01585 -0.0331 1.0000 0.1219
-3.000 -0.1853 0.02410 0.01347 -0.0325 1.0000 0.1331
-2.750 -0.1573 0.02212 0.01137 -0.0317 1.0000 0.1534
-2.500 -0.1302 0.02030 0.00960 -0.0307 1.0000 0.1947
-2.250 -0.1033 0.01775 0.00781 -0.0298 1.0000 0.3204
-2.000 -0.0723 0.01403 0.00629 -0.0266 1.0000 1.0000
-1.750 -0.0464 0.01398 0.00570 -0.0262 1.0000 1.0000
-1.500 -0.0211 0.01395 0.00528 -0.0258 1.0000 1.0000
-1.250 0.0040 0.01394 0.00493 -0.0255 1.0000 1.0000
-1.000 0.0286 0.01396 0.00469 -0.0251 1.0000 1.0000
-0.750 0.0530 0.01400 0.00454 -0.0247 1.0000 1.0000
-0.500 0.0768 0.01407 0.00446 -0.0243 1.0000 1.0000
-0.250 0.1000 0.01419 0.00446 -0.0240 1.0000 1.0000
0.000 0.1224 0.01437 0.00453 -0.0238 1.0000 1.0000
0.250 0.1435 0.01465 0.00473 -0.0236 1.0000 1.0000
0.500 0.1637 0.01504 0.00506 -0.0236 1.0000 1.0000
0.750 0.1837 0.01555 0.00550 -0.0240 1.0000 1.0000
1.000 0.2033 0.01617 0.00607 -0.0246 1.0000 1.0000
1.250 0.2227 0.01691 0.00679 -0.0255 1.0000 1.0000
1.500 0.2976 0.01767 0.00760 -0.0362 0.9688 1.0000
1.750 0.3751 0.01805 0.00813 -0.0460 0.9303 1.0000
2.000 0.4344 0.01820 0.00841 -0.0511 0.8914 1.0000
2.250 0.4759 0.01837 0.00863 -0.0521 0.8529 1.0000
2.500 0.5056 0.01863 0.00894 -0.0505 0.8159 1.0000
2.750 0.5289 0.01907 0.00934 -0.0480 0.7784 1.0000
3.000 0.5510 0.01955 0.00977 -0.0452 0.7434 1.0000
3.250 0.5726 0.02017 0.01035 -0.0426 0.7071 1.0000
3.500 0.5942 0.02084 0.01100 -0.0403 0.6697 1.0000
3.750 0.6161 0.02135 0.01152 -0.0378 0.6347 1.0000
4.000 0.6383 0.02183 0.01200 -0.0357 0.5980 1.0000
4.250 0.6609 0.02228 0.01240 -0.0335 0.5624 1.0000
4.500 0.6838 0.02276 0.01282 -0.0314 0.5263 1.0000
4.750 0.7069 0.02337 0.01345 -0.0296 0.4893 1.0000
5.000 0.7302 0.02398 0.01393 -0.0277 0.4542 1.0000
5.250 0.7536 0.02485 0.01482 -0.0263 0.4172 1.0000
5.500 0.7771 0.02569 0.01550 -0.0248 0.3838 1.0000
5.750 0.8004 0.02683 0.01673 -0.0236 0.3487 1.0000
6.000 0.8239 0.02801 0.01794 -0.0224 0.3174 1.0000
6.250 0.8472 0.02934 0.01924 -0.0213 0.2879 1.0000
6.500 0.8702 0.03080 0.02072 -0.0202 0.2597 1.0000
6.750 0.8928 0.03275 0.02288 -0.0193 0.2345 1.0000
7.000 0.9143 0.03465 0.02495 -0.0184 0.2098 1.0000
7.250 0.9368 0.03692 0.02732 -0.0174 0.1907 1.0000
7.500 0.9554 0.03969 0.03050 -0.0166 0.1715 1.0000
7.750 0.9735 0.04314 0.03433 -0.0159 0.1582 1.0000
8.000 0.9903 0.04665 0.03815 -0.0152 0.1464 1.0000
8.250 1.0061 0.04986 0.04155 -0.0145 0.1342 1.0000
8.500 1.0079 0.05627 0.04878 -0.0150 0.1318 1.0000
8.750 1.0038 0.06318 0.05624 -0.0163 0.1313 1.0000
9.000 0.9940 0.07042 0.06383 -0.0186 0.1321 1.0000
9.250 0.9822 0.07761 0.07121 -0.0214 0.1335 1.0000
9.500 0.9723 0.08453 0.07822 -0.0242 0.1347 1.0000
9.750 0.8815 0.10944 0.10274 -0.0520 0.1854 1.0000
10.000 0.8903 0.11325 0.10662 -0.0511 0.1773 1.0000
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Polar data table (+)
Polar graphs
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