AG45ct -02f (ag45ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG45ct -02f (ag45ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 45.27 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag45ct02r-il-100000.txt Download as CSV file: xf-ag45ct02r-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG45ct -02f
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5574 0.10401 0.09935 0.0153 1.0000 0.0770
-8.000 -0.5630 0.10104 0.09648 0.0080 1.0000 0.0786
-7.750 -0.5621 0.09671 0.09216 -0.0050 1.0000 0.0792
-7.500 -0.5451 0.09248 0.08797 0.0103 1.0000 0.0847
-7.250 -0.5401 0.08876 0.08429 0.0064 1.0000 0.0893
-7.000 -0.5331 0.08333 0.07873 -0.0139 1.0000 0.0928
-6.750 -0.5239 0.07941 0.07497 -0.0036 1.0000 0.0963
-6.500 -0.5115 0.07564 0.07119 -0.0058 1.0000 0.1019
-6.250 -0.4978 0.06972 0.06516 -0.0156 1.0000 0.1084
-6.000 -0.4842 0.06658 0.06207 -0.0136 1.0000 0.1132
-5.750 -0.4668 0.06142 0.05677 -0.0202 1.0000 0.1228
-5.500 -0.4475 0.05737 0.05251 -0.0246 1.0000 0.1355
-5.250 -0.4316 0.05411 0.04937 -0.0225 1.0000 0.1410
-5.000 -0.4118 0.05033 0.04548 -0.0246 1.0000 0.1540
-4.750 -0.3893 0.04701 0.04188 -0.0278 1.0000 0.1775
-4.500 -0.3695 0.04370 0.03857 -0.0277 1.0000 0.1926
-4.250 -0.3140 0.02974 0.02254 -0.0333 1.0000 0.0623
-4.000 -0.2864 0.02591 0.01810 -0.0330 1.0000 0.0568
-3.750 -0.2596 0.02368 0.01548 -0.0325 1.0000 0.0588
-3.500 -0.2322 0.02169 0.01310 -0.0319 1.0000 0.0617
-3.250 -0.2044 0.01971 0.01078 -0.0311 1.0000 0.0635
-3.000 -0.1775 0.01782 0.00876 -0.0303 1.0000 0.0684
-2.750 -0.1515 0.01648 0.00745 -0.0296 1.0000 0.0821
-2.500 -0.1259 0.01512 0.00624 -0.0289 1.0000 0.1078
-2.250 -0.1015 0.01308 0.00502 -0.0283 1.0000 0.2297
-2.000 -0.0888 0.01052 0.00479 -0.0245 1.0000 0.7437
-1.750 -0.0430 0.01001 0.00428 -0.0267 1.0000 1.0000
-1.500 -0.0186 0.01001 0.00402 -0.0262 1.0000 1.0000
-1.250 0.0054 0.01004 0.00383 -0.0257 1.0000 1.0000
-1.000 0.0288 0.01012 0.00375 -0.0254 1.0000 1.0000
-0.750 0.0510 0.01026 0.00377 -0.0250 1.0000 1.0000
-0.500 0.0716 0.01053 0.00391 -0.0248 1.0000 1.0000
-0.250 0.1130 0.01080 0.00403 -0.0286 0.9882 1.0000
0.000 0.1723 0.01091 0.00403 -0.0352 0.9666 1.0000
0.250 0.2245 0.01095 0.00398 -0.0399 0.9414 1.0000
0.500 0.2670 0.01098 0.00393 -0.0424 0.9122 1.0000
0.750 0.3000 0.01107 0.00391 -0.0427 0.8807 1.0000
1.000 0.3274 0.01120 0.00394 -0.0417 0.8500 1.0000
1.250 0.3526 0.01139 0.00401 -0.0404 0.8207 1.0000
1.500 0.3768 0.01163 0.00411 -0.0389 0.7923 1.0000
1.750 0.4008 0.01190 0.00426 -0.0374 0.7647 1.0000
2.000 0.4248 0.01222 0.00444 -0.0361 0.7379 1.0000
2.250 0.4490 0.01257 0.00466 -0.0348 0.7116 1.0000
2.500 0.4736 0.01290 0.00495 -0.0337 0.6839 1.0000
2.750 0.4984 0.01316 0.00514 -0.0326 0.6564 1.0000
3.000 0.5233 0.01336 0.00527 -0.0316 0.6290 1.0000
3.250 0.5484 0.01356 0.00540 -0.0305 0.6010 1.0000
3.500 0.5735 0.01378 0.00559 -0.0296 0.5722 1.0000
3.750 0.5986 0.01405 0.00577 -0.0287 0.5427 1.0000
4.000 0.6238 0.01435 0.00599 -0.0278 0.5128 1.0000
4.250 0.6488 0.01470 0.00624 -0.0270 0.4827 1.0000
4.500 0.6739 0.01510 0.00658 -0.0262 0.4527 1.0000
4.750 0.6990 0.01553 0.00696 -0.0255 0.4213 1.0000
5.000 0.7239 0.01601 0.00739 -0.0248 0.3897 1.0000
5.250 0.7487 0.01654 0.00785 -0.0242 0.3585 1.0000
5.500 0.7732 0.01713 0.00834 -0.0235 0.3277 1.0000
5.750 0.7975 0.01779 0.00898 -0.0229 0.2970 1.0000
6.000 0.8217 0.01850 0.00967 -0.0223 0.2662 1.0000
6.250 0.8457 0.01927 0.01041 -0.0217 0.2368 1.0000
6.500 0.8693 0.02014 0.01125 -0.0211 0.2090 1.0000
6.750 0.8925 0.02109 0.01221 -0.0205 0.1821 1.0000
7.000 0.9153 0.02223 0.01330 -0.0198 0.1577 1.0000
7.250 0.9375 0.02347 0.01446 -0.0192 0.1346 1.0000
7.500 0.9596 0.02492 0.01606 -0.0184 0.1137 1.0000
7.750 0.9814 0.02656 0.01770 -0.0176 0.0971 1.0000
8.000 1.0026 0.02834 0.01952 -0.0169 0.0833 1.0000
8.250 1.0239 0.03064 0.02212 -0.0159 0.0733 1.0000
8.500 1.0436 0.03322 0.02495 -0.0150 0.0654 1.0000
8.750 1.0630 0.03542 0.02733 -0.0142 0.0589 1.0000
9.000 1.0784 0.03965 0.03195 -0.0132 0.0559 1.0000
9.250 1.0894 0.04332 0.03634 -0.0119 0.0530 1.0000
9.500 1.1007 0.04632 0.03970 -0.0111 0.0493 1.0000
9.750 1.1099 0.04985 0.04348 -0.0103 0.0473 1.0000
10.000 1.1110 0.05462 0.04864 -0.0096 0.0467 1.0000
10.250 1.1039 0.05975 0.05423 -0.0091 0.0468 1.0000
10.500 1.0742 0.06608 0.06115 -0.0097 0.0482 1.0000
10.750 1.0326 0.07391 0.06932 -0.0146 0.0501 1.0000
11.000 0.9972 0.08413 0.07969 -0.0236 0.0525 1.0000
11.250 0.9737 0.09396 0.08954 -0.0306 0.0548 1.0000
11.500 0.9580 0.10249 0.09805 -0.0354 0.0560 1.0000
11.750 0.9468 0.11018 0.10572 -0.0388 0.0567 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG45ct -02f (ag45ct02r-il)