AG455ct -02f rot. (ag455ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: AG455ct -02f rot. (ag455ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 45.98 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag455ct02r-il-100000-n5.txt Download as CSV file: xf-ag455ct02r-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5810 0.11822 0.11334 0.0223 1.0000 0.0412
-9.000 -0.5797 0.11475 0.10992 0.0185 1.0000 0.0417
-8.750 -0.5771 0.11103 0.10624 0.0152 1.0000 0.0419
-8.500 -0.5739 0.10713 0.10239 0.0120 1.0000 0.0420
-8.250 -0.5705 0.10305 0.09836 0.0086 1.0000 0.0421
-8.000 -0.5657 0.09868 0.09402 0.0044 1.0000 0.0422
-7.750 -0.5575 0.09380 0.08915 -0.0006 1.0000 0.0422
-7.500 -0.5477 0.08879 0.08414 -0.0049 1.0000 0.0422
-7.250 -0.5435 0.08347 0.07884 0.0024 1.0000 0.0289
-7.000 -0.5342 0.07870 0.07409 -0.0016 1.0000 0.0283
-6.750 -0.5225 0.07354 0.06891 -0.0066 1.0000 0.0279
-6.500 -0.5086 0.06812 0.06344 -0.0118 1.0000 0.0276
-6.250 -0.4926 0.06255 0.05775 -0.0166 1.0000 0.0272
-6.000 -0.4747 0.05684 0.05189 -0.0210 1.0000 0.0263
-5.750 -0.4547 0.05069 0.04550 -0.0250 1.0000 0.0249
-5.500 -0.4320 0.04353 0.03791 -0.0287 1.0000 0.0231
-5.250 -0.4067 0.03677 0.03041 -0.0309 1.0000 0.0217
-5.000 -0.3820 0.03286 0.02597 -0.0315 1.0000 0.0214
-4.750 -0.3570 0.02943 0.02203 -0.0318 1.0000 0.0214
-4.500 -0.3315 0.02639 0.01851 -0.0319 1.0000 0.0216
-4.250 -0.3054 0.02385 0.01558 -0.0317 1.0000 0.0221
-4.000 -0.2791 0.02184 0.01327 -0.0315 1.0000 0.0230
-3.750 -0.2527 0.02048 0.01170 -0.0312 1.0000 0.0256
-3.500 -0.2258 0.01919 0.01014 -0.0307 1.0000 0.0290
-3.250 -0.1992 0.01778 0.00855 -0.0300 1.0000 0.0309
-3.000 -0.1735 0.01642 0.00720 -0.0296 1.0000 0.0349
-2.750 -0.1473 0.01555 0.00627 -0.0292 1.0000 0.0437
-2.500 -0.1210 0.01464 0.00536 -0.0288 1.0000 0.0571
-2.250 -0.0948 0.01376 0.00462 -0.0285 1.0000 0.0948
-2.000 -0.0693 0.01279 0.00420 -0.0284 1.0000 0.1990
-1.750 -0.0447 0.01180 0.00395 -0.0282 1.0000 0.3797
-1.500 -0.0256 0.01054 0.00387 -0.0260 1.0000 0.6851
-1.250 0.0078 0.00987 0.00362 -0.0257 1.0000 1.0000
-1.000 0.0359 0.00990 0.00346 -0.0260 0.9957 1.0000
-0.750 0.0790 0.00995 0.00329 -0.0292 0.9611 1.0000
-0.500 0.1202 0.01001 0.00314 -0.0318 0.9189 1.0000
-0.250 0.1585 0.01008 0.00298 -0.0336 0.8724 1.0000
0.000 0.1905 0.01020 0.00286 -0.0339 0.8284 1.0000
0.250 0.2182 0.01037 0.00279 -0.0333 0.7909 1.0000
0.500 0.2446 0.01057 0.00275 -0.0325 0.7603 1.0000
0.750 0.2709 0.01078 0.00277 -0.0318 0.7339 1.0000
1.000 0.2973 0.01100 0.00282 -0.0311 0.7106 1.0000
1.250 0.3237 0.01121 0.00291 -0.0306 0.6871 1.0000
1.500 0.3503 0.01140 0.00301 -0.0301 0.6629 1.0000
1.750 0.3768 0.01158 0.00310 -0.0296 0.6379 1.0000
2.000 0.4033 0.01176 0.00319 -0.0291 0.6122 1.0000
2.250 0.4297 0.01195 0.00329 -0.0286 0.5858 1.0000
2.500 0.4560 0.01216 0.00343 -0.0281 0.5586 1.0000
2.750 0.4822 0.01239 0.00356 -0.0275 0.5305 1.0000
3.000 0.5084 0.01264 0.00372 -0.0271 0.5018 1.0000
3.250 0.5346 0.01292 0.00390 -0.0266 0.4727 1.0000
3.500 0.5607 0.01322 0.00412 -0.0262 0.4433 1.0000
3.750 0.5868 0.01355 0.00441 -0.0258 0.4140 1.0000
4.000 0.6128 0.01391 0.00469 -0.0254 0.3848 1.0000
4.250 0.6387 0.01429 0.00501 -0.0250 0.3560 1.0000
4.500 0.6646 0.01471 0.00537 -0.0247 0.3275 1.0000
4.750 0.6904 0.01515 0.00581 -0.0243 0.2995 1.0000
5.000 0.7160 0.01563 0.00625 -0.0240 0.2725 1.0000
5.250 0.7416 0.01614 0.00674 -0.0237 0.2460 1.0000
5.500 0.7670 0.01668 0.00728 -0.0234 0.2209 1.0000
5.750 0.7923 0.01727 0.00791 -0.0231 0.1972 1.0000
6.000 0.8171 0.01793 0.00854 -0.0228 0.1755 1.0000
6.250 0.8421 0.01859 0.00926 -0.0225 0.1544 1.0000
6.500 0.8663 0.01937 0.01003 -0.0222 0.1357 1.0000
6.750 0.8907 0.02015 0.01089 -0.0218 0.1177 1.0000
7.000 0.9146 0.02103 0.01188 -0.0214 0.1014 1.0000
7.250 0.9379 0.02199 0.01290 -0.0210 0.0867 1.0000
7.500 0.9608 0.02306 0.01406 -0.0206 0.0740 1.0000
7.750 0.9830 0.02423 0.01533 -0.0201 0.0626 1.0000
8.000 1.0042 0.02562 0.01685 -0.0195 0.0542 1.0000
8.250 1.0243 0.02707 0.01833 -0.0190 0.0463 1.0000
8.500 1.0448 0.02868 0.02030 -0.0181 0.0408 1.0000
8.750 1.0626 0.03045 0.02213 -0.0175 0.0359 1.0000
9.000 1.0815 0.03231 0.02434 -0.0167 0.0319 1.0000
9.250 1.0983 0.03448 0.02677 -0.0158 0.0292 1.0000
9.500 1.1130 0.03667 0.02911 -0.0151 0.0270 1.0000
9.750 1.1247 0.03956 0.03232 -0.0142 0.0249 1.0000
10.000 1.1351 0.04241 0.03562 -0.0134 0.0229 1.0000
10.250 1.1407 0.04580 0.03942 -0.0126 0.0218 1.0000
10.500 1.1416 0.04945 0.04344 -0.0120 0.0210 1.0000
10.750 1.1366 0.05330 0.04761 -0.0116 0.0205 1.0000
11.000 1.1246 0.05741 0.05200 -0.0118 0.0203 1.0000
11.250 1.1089 0.06270 0.05755 -0.0146 0.0202 1.0000
11.500 1.0897 0.06962 0.06472 -0.0197 0.0204 1.0000
11.750 1.0659 0.07857 0.07390 -0.0269 0.0208 1.0000
12.000 1.0364 0.08998 0.08548 -0.0358 0.0215 1.0000
12.250 1.0008 0.10391 0.09949 -0.0452 0.0226 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG455ct -02f rot. (ag455ct02r-il)