AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 34.63 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-50000-n5.txt Download as CSV file: xf-ag44ct02r-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4308 0.09426 0.08784 -0.0029 1.0000 0.0574
-8.250 -0.4301 0.08999 0.08362 -0.0041 1.0000 0.0554
-8.000 -0.5340 0.09516 0.08850 -0.0014 1.0000 0.0476
-7.750 -0.5280 0.09121 0.08459 -0.0022 1.0000 0.0465
-7.500 -0.5221 0.08680 0.08023 -0.0053 1.0000 0.0456
-7.250 -0.5151 0.08206 0.07552 -0.0093 1.0000 0.0449
-7.000 -0.5067 0.07707 0.07053 -0.0136 1.0000 0.0443
-6.750 -0.4968 0.07191 0.06534 -0.0180 1.0000 0.0438
-6.500 -0.4853 0.06666 0.06001 -0.0221 1.0000 0.0434
-6.250 -0.4720 0.06141 0.05462 -0.0258 1.0000 0.0431
-6.000 -0.4569 0.05626 0.04927 -0.0289 1.0000 0.0427
-5.750 -0.4398 0.05124 0.04395 -0.0315 1.0000 0.0422
-5.500 -0.4207 0.04638 0.03869 -0.0335 1.0000 0.0416
-5.250 -0.3997 0.04197 0.03378 -0.0347 1.0000 0.0412
-5.000 -0.3771 0.03804 0.02935 -0.0353 1.0000 0.0412
-4.750 -0.3533 0.03460 0.02539 -0.0355 1.0000 0.0417
-4.500 -0.3284 0.03167 0.02196 -0.0353 1.0000 0.0433
-4.250 -0.3024 0.02926 0.01897 -0.0349 1.0000 0.0470
-4.000 -0.2771 0.02702 0.01643 -0.0344 1.0000 0.0506
-3.750 -0.2517 0.02517 0.01438 -0.0337 1.0000 0.0543
-3.500 -0.2256 0.02364 0.01245 -0.0327 1.0000 0.0614
-3.250 -0.2007 0.02220 0.01102 -0.0320 1.0000 0.0720
-3.000 -0.1751 0.02092 0.00964 -0.0313 1.0000 0.0887
-2.750 -0.1496 0.01961 0.00847 -0.0309 1.0000 0.1216
-2.500 -0.1245 0.01810 0.00749 -0.0308 1.0000 0.2135
-2.250 -0.1033 0.01642 0.00694 -0.0301 1.0000 0.4322
-2.000 -0.0903 0.01499 0.00678 -0.0255 1.0000 0.7332
-1.750 -0.0439 0.01445 0.00613 -0.0280 1.0000 1.0000
-1.500 -0.0212 0.01446 0.00581 -0.0274 1.0000 1.0000
-1.250 0.0013 0.01451 0.00556 -0.0268 1.0000 1.0000
-1.000 0.0232 0.01461 0.00542 -0.0263 1.0000 1.0000
-0.750 0.0445 0.01475 0.00538 -0.0257 1.0000 1.0000
-0.500 0.0710 0.01497 0.00540 -0.0263 0.9954 1.0000
-0.250 0.1193 0.01518 0.00537 -0.0309 0.9722 1.0000
0.000 0.1659 0.01535 0.00537 -0.0349 0.9484 1.0000
0.250 0.2095 0.01549 0.00538 -0.0380 0.9233 1.0000
0.500 0.2503 0.01561 0.00537 -0.0404 0.8970 1.0000
0.750 0.2877 0.01572 0.00538 -0.0418 0.8698 1.0000
1.000 0.3214 0.01586 0.00541 -0.0424 0.8424 1.0000
1.250 0.3517 0.01602 0.00548 -0.0423 0.8148 1.0000
1.500 0.3796 0.01622 0.00557 -0.0416 0.7876 1.0000
1.750 0.4060 0.01646 0.00569 -0.0406 0.7610 1.0000
2.000 0.4316 0.01673 0.00586 -0.0396 0.7351 1.0000
2.250 0.4568 0.01704 0.00610 -0.0384 0.7101 1.0000
2.500 0.4816 0.01737 0.00638 -0.0374 0.6831 1.0000
2.750 0.5061 0.01767 0.00666 -0.0363 0.6556 1.0000
3.000 0.5307 0.01796 0.00692 -0.0353 0.6280 1.0000
3.250 0.5552 0.01824 0.00717 -0.0342 0.6002 1.0000
3.500 0.5797 0.01854 0.00749 -0.0331 0.5719 1.0000
3.750 0.6041 0.01886 0.00778 -0.0321 0.5433 1.0000
4.000 0.6285 0.01922 0.00811 -0.0311 0.5146 1.0000
4.250 0.6530 0.01962 0.00848 -0.0302 0.4859 1.0000
4.500 0.6778 0.02008 0.00897 -0.0294 0.4577 1.0000
4.750 0.7025 0.02058 0.00946 -0.0287 0.4299 1.0000
5.000 0.7270 0.02113 0.01001 -0.0279 0.4029 1.0000
5.250 0.7513 0.02174 0.01062 -0.0272 0.3768 1.0000
5.500 0.7754 0.02239 0.01132 -0.0265 0.3518 1.0000
5.750 0.7993 0.02308 0.01208 -0.0259 0.3269 1.0000
6.000 0.8230 0.02383 0.01291 -0.0252 0.3023 1.0000
6.250 0.8462 0.02463 0.01377 -0.0245 0.2794 1.0000
6.500 0.8690 0.02548 0.01468 -0.0238 0.2564 1.0000
6.750 0.8915 0.02640 0.01578 -0.0231 0.2331 1.0000
7.000 0.9132 0.02738 0.01682 -0.0224 0.2113 1.0000
7.250 0.9344 0.02844 0.01801 -0.0216 0.1886 1.0000
7.500 0.9548 0.02962 0.01931 -0.0209 0.1665 1.0000
7.750 0.9741 0.03090 0.02064 -0.0200 0.1462 1.0000
8.000 0.9929 0.03241 0.02238 -0.0192 0.1260 1.0000
8.250 1.0103 0.03405 0.02412 -0.0184 0.1085 1.0000
8.500 1.0269 0.03591 0.02608 -0.0175 0.0943 1.0000
8.750 1.0425 0.03796 0.02830 -0.0165 0.0820 1.0000
9.000 1.0571 0.04031 0.03092 -0.0155 0.0721 1.0000
9.250 1.0706 0.04284 0.03356 -0.0145 0.0656 1.0000
9.500 1.0816 0.04546 0.03654 -0.0135 0.0587 1.0000
9.750 1.0912 0.04827 0.03947 -0.0126 0.0543 1.0000
10.000 1.0960 0.05223 0.04397 -0.0116 0.0515 1.0000
10.250 1.0964 0.05600 0.04813 -0.0108 0.0489 1.0000
10.500 1.0953 0.05926 0.05167 -0.0103 0.0465 1.0000
11.000 1.0803 0.06667 0.05934 -0.0100 0.0437 1.0000
11.250 1.0632 0.07207 0.06502 -0.0122 0.0436 1.0000
11.500 1.0452 0.07834 0.07150 -0.0159 0.0437 1.0000
11.750 1.0266 0.08539 0.07863 -0.0204 0.0439 1.0000
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Polar data table (+)
Polar graphs
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