AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 500,000 Max Cl/Cd: 82.14 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-500000.txt Download as CSV file: xf-ag44ct02r-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5471 0.09322 0.09108 0.0108 1.0000 0.0143
-8.000 -0.5439 0.08928 0.08715 0.0084 1.0000 0.0146
-7.750 -0.5411 0.08518 0.08309 0.0055 1.0000 0.0149
-7.500 -0.5376 0.08077 0.07870 0.0015 1.0000 0.0152
-7.250 -0.5285 0.07542 0.07336 -0.0049 1.0000 0.0156
-7.000 -0.5160 0.06936 0.06728 -0.0125 1.0000 0.0162
-6.750 -0.4984 0.06236 0.06021 -0.0207 1.0000 0.0170
-6.500 -0.4739 0.05567 0.05336 -0.0272 1.0000 0.0177
-6.250 -0.4555 0.04960 0.04708 -0.0310 1.0000 0.0179
-6.000 -0.4384 0.04427 0.04146 -0.0333 1.0000 0.0179
-5.750 -0.4318 0.03548 0.03236 -0.0360 1.0000 0.0192
-5.500 -0.4120 0.03317 0.02995 -0.0362 1.0000 0.0199
-5.250 -0.3912 0.03057 0.02715 -0.0362 1.0000 0.0211
-5.000 -0.3690 0.02771 0.02401 -0.0359 1.0000 0.0232
-4.750 -0.3406 0.02828 0.02423 -0.0345 1.0000 0.0260
-4.500 -0.3235 0.01807 0.01314 -0.0334 1.0000 0.0162
-4.250 -0.2990 0.01658 0.01141 -0.0325 1.0000 0.0168
-4.000 -0.2744 0.01430 0.00881 -0.0316 1.0000 0.0159
-3.750 -0.2493 0.01264 0.00694 -0.0307 1.0000 0.0152
-3.500 -0.2241 0.01148 0.00566 -0.0299 1.0000 0.0152
-3.250 -0.1988 0.01063 0.00472 -0.0292 1.0000 0.0158
-2.750 -0.1194 0.00898 0.00292 -0.0340 0.9856 0.0221
-2.500 -0.0804 0.00838 0.00234 -0.0362 0.9714 0.0409
-2.250 -0.0439 0.00769 0.00199 -0.0381 0.9481 0.1261
-2.000 -0.0115 0.00719 0.00178 -0.0390 0.9092 0.2242
-1.750 0.0135 0.00679 0.00162 -0.0383 0.8578 0.3395
-1.250 0.0602 0.00595 0.00146 -0.0362 0.7833 0.6461
-1.000 0.0812 0.00552 0.00145 -0.0343 0.7608 0.8004
-0.750 0.1124 0.00529 0.00144 -0.0341 0.7428 0.9648
-0.500 0.1519 0.00537 0.00135 -0.0365 0.7262 1.0000
-0.250 0.1787 0.00548 0.00132 -0.0362 0.7120 1.0000
0.000 0.2057 0.00558 0.00131 -0.0358 0.6987 1.0000
0.250 0.2329 0.00564 0.00130 -0.0356 0.6837 1.0000
0.500 0.2602 0.00570 0.00127 -0.0353 0.6681 1.0000
0.750 0.2874 0.00577 0.00125 -0.0350 0.6508 1.0000
1.000 0.3145 0.00584 0.00123 -0.0347 0.6319 1.0000
1.250 0.3417 0.00594 0.00123 -0.0345 0.6107 1.0000
1.500 0.3687 0.00605 0.00124 -0.0342 0.5880 1.0000
1.750 0.3957 0.00619 0.00126 -0.0339 0.5636 1.0000
2.000 0.4227 0.00634 0.00130 -0.0336 0.5370 1.0000
2.250 0.4496 0.00651 0.00137 -0.0334 0.5096 1.0000
2.500 0.4765 0.00670 0.00144 -0.0331 0.4816 1.0000
2.750 0.5034 0.00690 0.00152 -0.0329 0.4537 1.0000
3.000 0.5303 0.00711 0.00163 -0.0327 0.4265 1.0000
3.250 0.5572 0.00733 0.00176 -0.0325 0.4002 1.0000
3.500 0.5841 0.00756 0.00190 -0.0323 0.3756 1.0000
3.750 0.6109 0.00781 0.00205 -0.0321 0.3513 1.0000
4.000 0.6377 0.00805 0.00221 -0.0319 0.3281 1.0000
4.250 0.6645 0.00830 0.00240 -0.0317 0.3058 1.0000
4.500 0.6912 0.00857 0.00260 -0.0316 0.2842 1.0000
4.750 0.7180 0.00882 0.00281 -0.0314 0.2636 1.0000
5.000 0.7446 0.00911 0.00303 -0.0312 0.2432 1.0000
5.250 0.7712 0.00940 0.00328 -0.0310 0.2236 1.0000
5.500 0.7976 0.00971 0.00354 -0.0308 0.2037 1.0000
5.750 0.8239 0.01005 0.00382 -0.0306 0.1847 1.0000
6.000 0.8502 0.01038 0.00412 -0.0304 0.1654 1.0000
6.250 0.8761 0.01078 0.00444 -0.0302 0.1464 1.0000
6.500 0.9021 0.01116 0.00481 -0.0300 0.1285 1.0000
6.750 0.9277 0.01159 0.00519 -0.0298 0.1099 1.0000
7.000 0.9530 0.01208 0.00562 -0.0295 0.0916 1.0000
7.250 0.9782 0.01259 0.00608 -0.0292 0.0739 1.0000
7.500 1.0026 0.01324 0.00664 -0.0289 0.0562 1.0000
7.750 1.0269 0.01390 0.00730 -0.0285 0.0421 1.0000
8.000 1.0507 0.01469 0.00808 -0.0280 0.0318 1.0000
8.250 1.0729 0.01576 0.00918 -0.0273 0.0242 1.0000
8.500 1.0973 0.01633 0.00984 -0.0269 0.0208 1.0000
8.750 1.1168 0.01782 0.01142 -0.0260 0.0168 1.0000
9.000 1.1402 0.01852 0.01225 -0.0254 0.0155 1.0000
9.250 1.1620 0.01946 0.01332 -0.0247 0.0140 1.0000
9.500 1.1826 0.02054 0.01449 -0.0240 0.0128 1.0000
9.750 1.1938 0.02315 0.01730 -0.0223 0.0114 1.0000
10.000 1.2149 0.02400 0.01829 -0.0217 0.0108 1.0000
10.250 1.2339 0.02512 0.01955 -0.0208 0.0100 1.0000
10.500 1.2503 0.02659 0.02118 -0.0198 0.0095 1.0000
10.750 1.2654 0.02811 0.02285 -0.0187 0.0090 1.0000
11.000 1.2788 0.02971 0.02459 -0.0175 0.0085 1.0000
11.250 1.2890 0.03157 0.02659 -0.0162 0.0082 1.0000
11.500 1.2926 0.03409 0.02933 -0.0146 0.0079 1.0000
11.750 1.2864 0.03720 0.03266 -0.0122 0.0077 1.0000
12.000 1.2736 0.04098 0.03670 -0.0105 0.0076 1.0000
12.250 1.2572 0.04574 0.04173 -0.0107 0.0075 1.0000
12.500 1.2421 0.05103 0.04727 -0.0127 0.0074 1.0000
12.750 1.1379 0.04280 0.03921 -0.0069 0.0078 1.0000
13.000 1.1206 0.04905 0.04562 -0.0086 0.0079 1.0000
13.250 1.1017 0.05587 0.05259 -0.0107 0.0079 1.0000
13.500 1.0815 0.06311 0.05997 -0.0129 0.0079 1.0000
13.750 1.0612 0.07048 0.06747 -0.0154 0.0079 1.0000
14.000 1.0415 0.07788 0.07501 -0.0180 0.0080 1.0000
14.250 1.0199 0.08564 0.08291 -0.0210 0.0081 1.0000
14.500 0.9964 0.09381 0.09120 -0.0243 0.0081 1.0000
14.750 0.9698 0.10246 0.10000 -0.0280 0.0083 1.0000
15.000 0.9376 0.11193 0.10963 -0.0322 0.0086 1.0000
15.250 0.8989 0.12216 0.12002 -0.0369 0.0090 1.0000
15.500 0.8430 0.13266 0.13066 -0.0417 0.0097 1.0000
15.750 0.7770 0.14765 0.14575 -0.0489 0.0108 1.0000
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Polar data table (+)
Polar graphs
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