AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 50,000 Max Cl/Cd: 30.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-50000.txt Download as CSV file: xf-ag44ct02r-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.5421 0.10107 0.09479 0.0107 1.0000 0.2284
-7.250 -0.5338 0.09723 0.09099 0.0107 1.0000 0.2424
-7.000 -0.5277 0.09366 0.08748 0.0099 1.0000 0.2566
-6.750 -0.5179 0.08957 0.08345 0.0106 1.0000 0.2717
-6.500 -0.5057 0.08549 0.07941 0.0120 1.0000 0.2874
-6.250 -0.4938 0.08176 0.07572 0.0132 1.0000 0.3047
-6.000 -0.4941 0.07913 0.07318 0.0102 1.0000 0.3283
-5.750 -0.4770 0.07499 0.06907 0.0139 1.0000 0.3477
-5.500 -0.4689 0.07175 0.06590 0.0147 1.0000 0.3745
-5.250 -0.4585 0.06850 0.06271 0.0168 1.0000 0.4038
-4.750 -0.3693 0.04420 0.03638 -0.0346 1.0000 0.1284
-4.500 -0.3419 0.03925 0.03075 -0.0360 1.0000 0.1148
-4.250 -0.3167 0.03566 0.02675 -0.0362 1.0000 0.1139
-4.000 -0.2898 0.03250 0.02299 -0.0362 1.0000 0.1149
-3.750 -0.2622 0.02960 0.01950 -0.0357 1.0000 0.1155
-3.500 -0.2359 0.02687 0.01662 -0.0352 1.0000 0.1199
-3.250 -0.2093 0.02486 0.01439 -0.0345 1.0000 0.1338
-3.000 -0.1821 0.02284 0.01225 -0.0335 1.0000 0.1505
-2.750 -0.1556 0.02100 0.01047 -0.0325 1.0000 0.1890
-2.500 -0.1292 0.01867 0.00875 -0.0316 1.0000 0.2968
-2.250 -0.0904 0.01453 0.00722 -0.0291 1.0000 1.0000
-2.000 -0.0668 0.01447 0.00658 -0.0286 1.0000 1.0000
-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 0.0651 0.01497 0.00542 -0.0252 1.0000 1.0000
-0.250 0.0853 0.01526 0.00556 -0.0249 1.0000 1.0000
0.000 0.1054 0.01563 0.00576 -0.0247 1.0000 1.0000
0.250 0.1252 0.01607 0.00608 -0.0246 1.0000 1.0000
0.500 0.1449 0.01658 0.00650 -0.0248 1.0000 1.0000
0.750 0.1645 0.01718 0.00702 -0.0252 1.0000 1.0000
1.000 0.1837 0.01786 0.00764 -0.0257 1.0000 1.0000
1.250 0.2412 0.01872 0.00847 -0.0333 0.9810 1.0000
1.500 0.3122 0.01936 0.00916 -0.0425 0.9494 1.0000
1.750 0.3825 0.01969 0.00960 -0.0506 0.9178 1.0000
2.000 0.4413 0.01978 0.00980 -0.0555 0.8862 1.0000
2.250 0.4829 0.01990 0.01002 -0.0566 0.8529 1.0000
2.500 0.5158 0.02006 0.01022 -0.0559 0.8196 1.0000
2.750 0.5442 0.02027 0.01043 -0.0541 0.7875 1.0000
3.000 0.5684 0.02064 0.01078 -0.0518 0.7548 1.0000
3.250 0.5910 0.02111 0.01124 -0.0493 0.7217 1.0000
3.500 0.6137 0.02162 0.01174 -0.0467 0.6904 1.0000
3.750 0.6353 0.02222 0.01238 -0.0447 0.6560 1.0000
4.000 0.6578 0.02266 0.01280 -0.0425 0.6244 1.0000
4.250 0.6807 0.02304 0.01315 -0.0403 0.5939 1.0000
4.500 0.7039 0.02345 0.01357 -0.0383 0.5636 1.0000
4.750 0.7269 0.02402 0.01416 -0.0366 0.5319 1.0000
5.000 0.7502 0.02460 0.01474 -0.0349 0.5012 1.0000
5.250 0.7737 0.02527 0.01540 -0.0333 0.4714 1.0000
5.500 0.7971 0.02605 0.01622 -0.0318 0.4421 1.0000
5.750 0.8204 0.02690 0.01707 -0.0304 0.4130 1.0000
6.000 0.8436 0.02789 0.01808 -0.0290 0.3846 1.0000
6.250 0.8666 0.02898 0.01921 -0.0277 0.3565 1.0000
6.500 0.8891 0.03014 0.02041 -0.0264 0.3284 1.0000
6.750 0.9112 0.03144 0.02183 -0.0252 0.3008 1.0000
7.000 0.9327 0.03290 0.02339 -0.0239 0.2736 1.0000
7.250 0.9535 0.03436 0.02491 -0.0225 0.2460 1.0000
7.500 0.9735 0.03618 0.02685 -0.0212 0.2202 1.0000
7.750 0.9933 0.03817 0.02891 -0.0199 0.1963 1.0000
8.000 1.0134 0.03985 0.03051 -0.0186 0.1727 1.0000
8.250 1.0288 0.04317 0.03428 -0.0174 0.1567 1.0000
8.500 1.0419 0.04633 0.03781 -0.0162 0.1416 1.0000
8.750 1.0570 0.04974 0.04138 -0.0152 0.1306 1.0000
9.000 1.0555 0.05550 0.04794 -0.0146 0.1266 1.0000
9.250 1.0684 0.05861 0.05108 -0.0136 0.1171 1.0000
9.500 1.0573 0.06473 0.05776 -0.0138 0.1158 1.0000
9.750 1.0417 0.07108 0.06447 -0.0147 0.1159 1.0000
10.000 1.0237 0.07749 0.07108 -0.0163 0.1167 1.0000
10.250 1.0057 0.08367 0.07735 -0.0182 0.1177 1.0000
10.500 0.9905 0.09026 0.08400 -0.0209 0.1184 1.0000
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Polar data table (+)
Polar graphs
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