AG44ct -02f (ag44ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: AG44ct -02f (ag44ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 60.6 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag44ct02r-il-200000-n5.txt Download as CSV file: xf-ag44ct02r-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5428 0.09318 0.08977 0.0077 1.0000 0.0167
-8.000 -0.5404 0.08921 0.08584 0.0060 1.0000 0.0154
-7.500 -0.5385 0.07547 0.07217 -0.0066 1.0000 0.0119
-7.250 -0.5301 0.06976 0.06645 -0.0127 1.0000 0.0117
-7.000 -0.5189 0.06350 0.06014 -0.0190 1.0000 0.0115
-6.750 -0.5057 0.05679 0.05331 -0.0248 1.0000 0.0113
-6.500 -0.4909 0.04986 0.04618 -0.0295 1.0000 0.0112
-6.250 -0.4742 0.04215 0.03811 -0.0329 1.0000 0.0116
-5.750 -0.4381 0.03057 0.02545 -0.0354 1.0000 0.0126
-5.500 -0.4163 0.02691 0.02125 -0.0353 1.0000 0.0125
-5.250 -0.3935 0.02403 0.01790 -0.0349 1.0000 0.0124
-5.000 -0.3700 0.02157 0.01501 -0.0344 1.0000 0.0125
-4.750 -0.3459 0.01952 0.01261 -0.0338 1.0000 0.0127
-4.500 -0.3213 0.01790 0.01076 -0.0332 1.0000 0.0130
-4.250 -0.2965 0.01662 0.00932 -0.0326 1.0000 0.0135
-4.000 -0.2716 0.01555 0.00812 -0.0319 1.0000 0.0142
-3.750 -0.2466 0.01459 0.00708 -0.0313 1.0000 0.0153
-3.500 -0.2215 0.01382 0.00621 -0.0306 1.0000 0.0169
-3.250 -0.1966 0.01307 0.00542 -0.0301 1.0000 0.0200
-3.000 -0.1672 0.01245 0.00475 -0.0304 0.9966 0.0236
-2.750 -0.1288 0.01176 0.00400 -0.0327 0.9833 0.0323
-2.500 -0.0923 0.01113 0.00346 -0.0345 0.9647 0.0588
-2.250 -0.0560 0.01050 0.00309 -0.0364 0.9408 0.1278
-2.000 -0.0211 0.00991 0.00284 -0.0381 0.9086 0.2266
-1.750 0.0107 0.00932 0.00262 -0.0389 0.8702 0.3537
-1.500 0.0372 0.00879 0.00246 -0.0384 0.8311 0.4964
-1.250 0.0601 0.00834 0.00236 -0.0369 0.7982 0.6366
-0.750 0.1164 0.00774 0.00221 -0.0350 0.7499 0.9442
-0.500 0.1538 0.00782 0.00206 -0.0368 0.7303 1.0000
-0.250 0.1801 0.00796 0.00200 -0.0363 0.7138 1.0000
0.000 0.2067 0.00809 0.00197 -0.0359 0.6985 1.0000
0.250 0.2336 0.00818 0.00195 -0.0356 0.6811 1.0000
0.500 0.2603 0.00829 0.00193 -0.0352 0.6634 1.0000
0.750 0.2872 0.00838 0.00192 -0.0348 0.6442 1.0000
1.000 0.3139 0.00849 0.00191 -0.0344 0.6238 1.0000
1.250 0.3406 0.00861 0.00192 -0.0341 0.6022 1.0000
1.500 0.3671 0.00875 0.00193 -0.0337 0.5791 1.0000
1.750 0.3937 0.00890 0.00196 -0.0333 0.5541 1.0000
2.000 0.4203 0.00907 0.00201 -0.0329 0.5285 1.0000
2.250 0.4467 0.00926 0.00210 -0.0325 0.5022 1.0000
2.500 0.4731 0.00947 0.00218 -0.0322 0.4756 1.0000
2.750 0.4996 0.00970 0.00230 -0.0319 0.4496 1.0000
3.250 0.5524 0.01019 0.00259 -0.0313 0.3986 1.0000
3.500 0.5788 0.01046 0.00279 -0.0310 0.3745 1.0000
3.750 0.6051 0.01074 0.00299 -0.0307 0.3515 1.0000
4.000 0.6315 0.01102 0.00321 -0.0305 0.3292 1.0000
4.250 0.6578 0.01133 0.00345 -0.0302 0.3082 1.0000
4.500 0.6840 0.01163 0.00375 -0.0299 0.2876 1.0000
4.750 0.7102 0.01197 0.00403 -0.0297 0.2677 1.0000
5.000 0.7363 0.01229 0.00434 -0.0294 0.2482 1.0000
5.250 0.7623 0.01266 0.00467 -0.0292 0.2289 1.0000
5.500 0.7882 0.01303 0.00506 -0.0289 0.2104 1.0000
5.750 0.8139 0.01343 0.00544 -0.0287 0.1917 1.0000
6.000 0.8394 0.01386 0.00586 -0.0284 0.1733 1.0000
6.250 0.8649 0.01431 0.00630 -0.0281 0.1552 1.0000
6.500 0.8901 0.01479 0.00681 -0.0278 0.1367 1.0000
6.750 0.9149 0.01535 0.00733 -0.0275 0.1189 1.0000
7.000 0.9396 0.01590 0.00790 -0.0272 0.1014 1.0000
7.250 0.9639 0.01654 0.00852 -0.0268 0.0840 1.0000
7.500 0.9876 0.01726 0.00922 -0.0264 0.0683 1.0000
7.750 1.0109 0.01804 0.01004 -0.0260 0.0542 1.0000
8.000 1.0338 0.01890 0.01092 -0.0255 0.0430 1.0000
8.250 1.0559 0.01988 0.01193 -0.0250 0.0339 1.0000
8.500 1.0782 0.02078 0.01298 -0.0244 0.0285 1.0000
8.750 1.0983 0.02203 0.01429 -0.0236 0.0239 1.0000
9.000 1.1197 0.02300 0.01543 -0.0230 0.0205 1.0000
9.250 1.1388 0.02428 0.01687 -0.0222 0.0181 1.0000
9.500 1.1546 0.02601 0.01875 -0.0211 0.0165 1.0000
9.750 1.1724 0.02739 0.02034 -0.0202 0.0152 1.0000
10.000 1.1895 0.02873 0.02186 -0.0193 0.0137 1.0000
10.250 1.2053 0.03012 0.02339 -0.0185 0.0124 1.0000
10.500 1.2153 0.03222 0.02564 -0.0172 0.0116 1.0000
10.750 1.2231 0.03453 0.02815 -0.0158 0.0111 1.0000
11.000 1.2311 0.03666 0.03053 -0.0144 0.0107 1.0000
11.250 1.2344 0.03900 0.03312 -0.0129 0.0103 1.0000
11.500 1.2333 0.04158 0.03594 -0.0113 0.0100 1.0000
11.750 1.2293 0.04460 0.03919 -0.0106 0.0098 1.0000
12.000 1.2232 0.04822 0.04305 -0.0111 0.0096 1.0000
12.250 1.2157 0.05245 0.04752 -0.0127 0.0094 1.0000
12.500 1.2066 0.05730 0.05263 -0.0152 0.0093 1.0000
12.750 1.1955 0.06280 0.05834 -0.0183 0.0092 1.0000
13.000 1.1819 0.06909 0.06484 -0.0221 0.0091 1.0000
13.250 1.1663 0.07611 0.07205 -0.0265 0.0091 1.0000
13.500 1.1481 0.08391 0.07999 -0.0314 0.0092 1.0000
13.750 1.1281 0.09237 0.08862 -0.0365 0.0093 1.0000
14.000 1.1056 0.10160 0.09800 -0.0419 0.0095 1.0000
14.250 1.0824 0.11133 0.10787 -0.0474 0.0097 1.0000
14.500 1.0577 0.12207 0.11872 -0.0535 0.0099 1.0000
14.750 1.0312 0.13394 0.13068 -0.0599 0.0102 1.0000
15.000 1.0021 0.14743 0.14422 -0.0669 0.0106 1.0000
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Polar data table (+)
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