AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 100,000 Max Cl/Cd: 45.73 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-100000.txt Download as CSV file: xf-ag44ct02r-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: AG44ct -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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5530 0.11742 0.11258 0.0148 1.0000 0.0733
-9.000 -0.5593 0.11498 0.11022 0.0090 1.0000 0.0743
-8.750 -0.5650 0.11213 0.10746 0.0029 1.0000 0.0746
-8.500 -0.5384 0.10549 0.10076 0.0117 1.0000 0.0790
-8.250 -0.5330 0.10201 0.09732 0.0105 1.0000 0.0822
-8.000 -0.5325 0.09860 0.09397 0.0072 1.0000 0.0857
-7.750 -0.5403 0.09526 0.09072 -0.0043 1.0000 0.0878
-7.500 -0.5343 0.08990 0.08541 -0.0059 1.0000 0.0893
-7.250 -0.5209 0.08671 0.08223 -0.0001 1.0000 0.0929
-7.000 -0.5125 0.08279 0.07830 -0.0037 1.0000 0.0975
-6.750 -0.5058 0.07644 0.07189 -0.0191 1.0000 0.1028
-6.500 -0.4937 0.07335 0.06888 -0.0134 1.0000 0.1059
-6.250 -0.4796 0.06816 0.06340 -0.0259 1.0000 0.1163
-6.000 -0.4670 0.06448 0.05992 -0.0212 1.0000 0.1192
-5.750 -0.4502 0.05996 0.05518 -0.0272 1.0000 0.1309
-5.500 -0.4350 0.05679 0.05212 -0.0250 1.0000 0.1356
-5.250 -0.4134 0.05375 0.04861 -0.0310 1.0000 0.1575
-5.000 -0.3984 0.04928 0.04438 -0.0292 1.0000 0.1614
-4.750 -0.3792 0.04603 0.04106 -0.0299 1.0000 0.1760
-4.500 -0.3281 0.03185 0.02465 -0.0360 1.0000 0.0606
-4.250 -0.3044 0.02825 0.02075 -0.0357 1.0000 0.0586
-4.000 -0.2786 0.02572 0.01771 -0.0350 1.0000 0.0596
-3.750 -0.2524 0.02332 0.01487 -0.0343 1.0000 0.0600
-3.500 -0.2258 0.02120 0.01235 -0.0334 1.0000 0.0606
-3.250 -0.1997 0.01899 0.00998 -0.0325 1.0000 0.0635
-3.000 -0.1741 0.01787 0.00878 -0.0318 1.0000 0.0740
-2.750 -0.1488 0.01630 0.00729 -0.0309 1.0000 0.0872
-2.500 -0.1243 0.01483 0.00613 -0.0302 1.0000 0.1236
-2.250 -0.1010 0.01242 0.00511 -0.0299 1.0000 0.3607
-2.000 -0.0883 0.01059 0.00508 -0.0251 1.0000 0.8065
-1.750 -0.0415 0.01030 0.00459 -0.0282 1.0000 1.0000
-1.500 -0.0185 0.01034 0.00438 -0.0276 1.0000 1.0000
-1.250 0.0038 0.01044 0.00425 -0.0271 1.0000 1.0000
-1.000 0.0253 0.01061 0.00425 -0.0266 1.0000 1.0000
-0.750 0.0458 0.01087 0.00437 -0.0263 1.0000 1.0000
-0.500 0.0728 0.01120 0.00455 -0.0274 0.9969 1.0000
-0.250 0.1308 0.01138 0.00456 -0.0339 0.9784 1.0000
0.000 0.1874 0.01146 0.00452 -0.0398 0.9598 1.0000
0.250 0.2382 0.01147 0.00445 -0.0442 0.9391 1.0000
0.500 0.2808 0.01146 0.00436 -0.0467 0.9149 1.0000
0.750 0.3159 0.01147 0.00430 -0.0474 0.8882 1.0000
1.000 0.3455 0.01153 0.00427 -0.0470 0.8608 1.0000
1.250 0.3719 0.01164 0.00428 -0.0458 0.8333 1.0000
1.500 0.3966 0.01180 0.00433 -0.0443 0.8058 1.0000
1.750 0.4208 0.01201 0.00443 -0.0428 0.7786 1.0000
2.000 0.4448 0.01227 0.00456 -0.0414 0.7516 1.0000
2.250 0.4689 0.01257 0.00476 -0.0400 0.7249 1.0000
2.500 0.4931 0.01291 0.00498 -0.0387 0.6978 1.0000
2.750 0.5175 0.01318 0.00519 -0.0375 0.6687 1.0000
3.000 0.5421 0.01339 0.00533 -0.0364 0.6401 1.0000
3.250 0.5668 0.01358 0.00545 -0.0353 0.6110 1.0000
3.500 0.5916 0.01380 0.00561 -0.0342 0.5811 1.0000
3.750 0.6163 0.01407 0.00576 -0.0332 0.5508 1.0000
4.000 0.6412 0.01439 0.00598 -0.0323 0.5193 1.0000
4.250 0.6660 0.01476 0.00626 -0.0315 0.4878 1.0000
4.500 0.6908 0.01519 0.00663 -0.0307 0.4573 1.0000
4.750 0.7157 0.01567 0.00702 -0.0299 0.4279 1.0000
5.000 0.7404 0.01619 0.00746 -0.0292 0.3994 1.0000
5.250 0.7651 0.01675 0.00797 -0.0286 0.3718 1.0000
5.500 0.7897 0.01734 0.00855 -0.0279 0.3449 1.0000
5.750 0.8142 0.01798 0.00915 -0.0273 0.3191 1.0000
6.000 0.8384 0.01865 0.00977 -0.0266 0.2941 1.0000
6.250 0.8624 0.01935 0.01042 -0.0260 0.2694 1.0000
6.500 0.8861 0.02006 0.01122 -0.0253 0.2442 1.0000
6.750 0.9094 0.02083 0.01203 -0.0247 0.2192 1.0000
7.000 0.9322 0.02169 0.01289 -0.0240 0.1946 1.0000
7.250 0.9543 0.02265 0.01380 -0.0232 0.1703 1.0000
7.500 0.9755 0.02370 0.01480 -0.0225 0.1455 1.0000
7.750 0.9965 0.02495 0.01615 -0.0216 0.1216 1.0000
8.000 1.0167 0.02663 0.01789 -0.0206 0.1021 1.0000
8.250 1.0366 0.02829 0.01967 -0.0196 0.0857 1.0000
8.500 1.0566 0.03055 0.02204 -0.0186 0.0747 1.0000
8.750 1.0755 0.03282 0.02436 -0.0177 0.0656 1.0000
9.000 1.0942 0.03518 0.02707 -0.0165 0.0592 1.0000
9.250 1.1107 0.03900 0.03099 -0.0157 0.0551 1.0000
9.500 1.1225 0.04184 0.03451 -0.0141 0.0515 1.0000
9.750 1.1339 0.04487 0.03790 -0.0129 0.0482 1.0000
10.000 1.1412 0.04865 0.04210 -0.0117 0.0468 1.0000
10.250 1.1434 0.05290 0.04673 -0.0106 0.0460 1.0000
10.500 1.1385 0.05758 0.05181 -0.0096 0.0458 1.0000
10.750 1.1238 0.06253 0.05719 -0.0088 0.0461 1.0000
11.000 1.0888 0.06817 0.06327 -0.0092 0.0473 1.0000
11.250 1.0500 0.07615 0.07151 -0.0148 0.0489 1.0000
11.500 1.0137 0.08650 0.08202 -0.0236 0.0508 1.0000
|
Polar data table (+)
Polar graphs
<< Back to AG44ct -02f (ag44ct02r-il)