AG47ct -02f rot. (ag47ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG47ct -02f rot. (ag47ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 52.1 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag47ct02r-il-200000.txt Download as CSV file: xf-ag47ct02r-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG47ct -02f rot.
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5277 0.13541 0.13203 0.0241 1.0000 0.0265
-10.750 -0.5276 0.13221 0.12884 0.0226 1.0000 0.0266
-8.750 -0.6291 0.11004 0.10662 0.0307 1.0000 0.0287
-8.500 -0.6232 0.10657 0.10313 0.0303 1.0000 0.0299
-8.250 -0.6187 0.10295 0.09953 0.0288 1.0000 0.0307
-8.000 -0.6144 0.09927 0.09588 0.0269 1.0000 0.0316
-7.750 -0.6104 0.09552 0.09216 0.0247 1.0000 0.0325
-7.500 -0.6062 0.09166 0.08833 0.0219 1.0000 0.0335
-7.250 -0.5993 0.08740 0.08410 0.0175 1.0000 0.0346
-7.000 -0.5872 0.08249 0.07919 0.0106 1.0000 0.0360
-6.750 -0.5626 0.07651 0.07312 -0.0025 1.0000 0.0377
-6.500 -0.5401 0.07135 0.06777 -0.0099 1.0000 0.0382
-6.250 -0.5273 0.06422 0.06052 -0.0145 1.0000 0.0387
-6.000 -0.5189 0.05963 0.05602 -0.0140 1.0000 0.0400
-5.750 -0.5033 0.05632 0.05269 -0.0147 1.0000 0.0416
-5.500 -0.4832 0.05250 0.04878 -0.0168 1.0000 0.0438
-5.250 -0.4582 0.04811 0.04417 -0.0199 1.0000 0.0475
-5.000 -0.4290 0.04234 0.03782 -0.0240 1.0000 0.0522
-4.750 -0.4093 0.03913 0.03467 -0.0243 1.0000 0.0544
-4.500 -0.3852 0.03624 0.03160 -0.0250 1.0000 0.0586
-4.250 -0.3578 0.03249 0.02737 -0.0262 1.0000 0.0667
-4.000 -0.3295 0.03157 0.02607 -0.0260 1.0000 0.0768
-3.750 -0.2963 0.02204 0.01566 -0.0253 1.0000 0.0332
-3.500 -0.2678 0.01920 0.01233 -0.0248 1.0000 0.0324
-3.250 -0.2399 0.01748 0.01028 -0.0243 1.0000 0.0348
-3.000 -0.2118 0.01550 0.00800 -0.0236 1.0000 0.0346
-2.750 -0.1842 0.01403 0.00636 -0.0229 1.0000 0.0362
-2.500 -0.1573 0.01256 0.00479 -0.0223 1.0000 0.0406
-2.250 -0.1304 0.01170 0.00395 -0.0219 1.0000 0.0522
-2.000 -0.1035 0.01070 0.00307 -0.0216 1.0000 0.0804
-1.750 -0.0776 0.00907 0.00246 -0.0218 1.0000 0.2955
-1.500 -0.0640 0.00707 0.00240 -0.0185 1.0000 0.7954
-1.250 -0.0248 0.00673 0.00212 -0.0199 1.0000 1.0000
-1.000 0.0017 0.00672 0.00196 -0.0196 1.0000 1.0000
-0.750 0.0283 0.00672 0.00184 -0.0193 1.0000 1.0000
-0.500 0.0547 0.00673 0.00176 -0.0190 1.0000 1.0000
-0.250 0.0811 0.00674 0.00170 -0.0187 1.0000 1.0000
0.000 0.1074 0.00677 0.00169 -0.0184 1.0000 1.0000
0.250 0.1335 0.00681 0.00171 -0.0181 1.0000 1.0000
0.500 0.1596 0.00687 0.00177 -0.0179 1.0000 1.0000
0.750 0.2025 0.00694 0.00184 -0.0213 0.9785 1.0000
1.000 0.2508 0.00698 0.00186 -0.0253 0.9276 1.0000
1.250 0.2856 0.00708 0.00183 -0.0260 0.8606 1.0000
1.500 0.3100 0.00731 0.00186 -0.0244 0.8029 1.0000
1.750 0.3339 0.00760 0.00192 -0.0230 0.7576 1.0000
2.000 0.3585 0.00791 0.00204 -0.0219 0.7199 1.0000
2.250 0.3839 0.00818 0.00218 -0.0211 0.6835 1.0000
2.500 0.4097 0.00837 0.00229 -0.0204 0.6419 1.0000
2.750 0.4353 0.00859 0.00239 -0.0196 0.5917 1.0000
3.000 0.4605 0.00890 0.00248 -0.0188 0.5303 1.0000
3.250 0.4856 0.00932 0.00261 -0.0182 0.4581 1.0000
3.500 0.5106 0.00986 0.00282 -0.0177 0.3764 1.0000
3.750 0.5359 0.01050 0.00311 -0.0174 0.2966 1.0000
4.000 0.5613 0.01119 0.00354 -0.0171 0.2311 1.0000
4.250 0.5868 0.01191 0.00400 -0.0169 0.1828 1.0000
4.500 0.6126 0.01260 0.00455 -0.0166 0.1496 1.0000
4.750 0.6383 0.01334 0.00517 -0.0164 0.1258 1.0000
5.000 0.6642 0.01399 0.00584 -0.0161 0.1067 1.0000
5.250 0.6898 0.01479 0.00663 -0.0157 0.0927 1.0000
5.500 0.7153 0.01558 0.00743 -0.0153 0.0800 1.0000
5.750 0.7405 0.01661 0.00851 -0.0149 0.0702 1.0000
6.000 0.7649 0.01796 0.00983 -0.0144 0.0616 1.0000
6.250 0.7910 0.01858 0.01065 -0.0140 0.0538 1.0000
6.500 0.8148 0.02056 0.01273 -0.0134 0.0488 1.0000
6.750 0.8402 0.02184 0.01427 -0.0128 0.0442 1.0000
7.000 0.8639 0.02322 0.01570 -0.0124 0.0394 1.0000
7.250 0.8861 0.02628 0.01922 -0.0117 0.0372 1.0000
7.500 0.9083 0.02904 0.02249 -0.0109 0.0356 1.0000
7.750 0.9273 0.03286 0.02692 -0.0101 0.0345 1.0000
8.000 0.9453 0.03599 0.03055 -0.0096 0.0323 1.0000
8.250 0.9629 0.03862 0.03344 -0.0093 0.0305 1.0000
8.500 0.9595 0.04836 0.04417 -0.0097 0.0319 1.0000
8.750 0.9470 0.05861 0.05503 -0.0122 0.0341 1.0000
9.000 0.9349 0.06669 0.06334 -0.0158 0.0355 1.0000
9.250 0.9204 0.07392 0.07072 -0.0205 0.0366 1.0000
9.500 0.9064 0.08086 0.07768 -0.0263 0.0377 1.0000
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Polar data table (+)
Polar graphs
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