AG46ct -02f rot. (ag46ct02r-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG46ct -02f rot. (ag46ct02r-il) Reynolds number: 200,000 Max Cl/Cd: 58.16 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag46ct02r-il-200000.txt Download as CSV file: xf-ag46ct02r-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: AG46ct -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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5868 0.10932 0.10589 0.0222 1.0000 0.0328
-8.500 -0.5839 0.10584 0.10245 0.0179 1.0000 0.0333
-8.250 -0.5805 0.10214 0.09879 0.0137 1.0000 0.0335
-8.000 -0.5758 0.09820 0.09489 0.0096 1.0000 0.0336
-7.750 -0.5671 0.09357 0.09028 0.0037 1.0000 0.0337
-7.500 -0.5557 0.08845 0.08514 -0.0026 1.0000 0.0338
-7.250 -0.5595 0.08202 0.07878 -0.0006 1.0000 0.0350
-7.000 -0.5507 0.07867 0.07541 -0.0002 1.0000 0.0360
-6.750 -0.5391 0.07484 0.07158 -0.0026 1.0000 0.0371
-6.500 -0.5251 0.07051 0.06722 -0.0064 1.0000 0.0385
-6.250 -0.5084 0.06574 0.06239 -0.0112 1.0000 0.0403
-6.000 -0.4872 0.06033 0.05686 -0.0172 1.0000 0.0431
-5.750 -0.4526 0.05543 0.05132 -0.0256 1.0000 0.0459
-5.500 -0.4434 0.04836 0.04441 -0.0268 1.0000 0.0478
-5.250 -0.4250 0.04553 0.04157 -0.0271 1.0000 0.0500
-5.000 -0.4021 0.04209 0.03796 -0.0285 1.0000 0.0540
-4.750 -0.3758 0.03722 0.03258 -0.0309 1.0000 0.0609
-4.500 -0.3538 0.03462 0.02998 -0.0310 1.0000 0.0644
-4.250 -0.3277 0.03136 0.02625 -0.0318 1.0000 0.0747
-4.000 -0.2931 0.02303 0.01682 -0.0309 1.0000 0.0368
-3.750 -0.2642 0.02059 0.01376 -0.0301 1.0000 0.0348
-3.500 -0.2367 0.01872 0.01164 -0.0294 1.0000 0.0331
-3.250 -0.2094 0.01653 0.00916 -0.0288 1.0000 0.0328
-3.000 -0.1822 0.01508 0.00750 -0.0281 1.0000 0.0334
-2.750 -0.1559 0.01316 0.00554 -0.0275 1.0000 0.0362
-2.500 -0.1294 0.01248 0.00486 -0.0271 1.0000 0.0449
-2.250 -0.1027 0.01141 0.00379 -0.0266 1.0000 0.0588
-2.000 -0.0762 0.00992 0.00294 -0.0266 1.0000 0.1734
-1.750 -0.0519 0.00851 0.00272 -0.0267 1.0000 0.4639
-1.500 -0.0391 0.00711 0.00276 -0.0222 1.0000 0.8717
-1.250 0.0008 0.00694 0.00249 -0.0243 1.0000 1.0000
-1.000 0.0267 0.00695 0.00236 -0.0240 1.0000 1.0000
-0.750 0.0526 0.00697 0.00229 -0.0237 1.0000 1.0000
-0.500 0.0784 0.00702 0.00226 -0.0235 1.0000 1.0000
-0.250 0.1209 0.00708 0.00223 -0.0268 0.9843 1.0000
0.000 0.1697 0.00710 0.00215 -0.0310 0.9465 1.0000
0.250 0.2109 0.00712 0.00205 -0.0333 0.8938 1.0000
0.500 0.2399 0.00724 0.00196 -0.0328 0.8395 1.0000
0.750 0.2647 0.00746 0.00194 -0.0316 0.7965 1.0000
1.000 0.2896 0.00771 0.00197 -0.0305 0.7626 1.0000
1.250 0.3150 0.00797 0.00204 -0.0297 0.7339 1.0000
1.500 0.3408 0.00824 0.00215 -0.0290 0.7086 1.0000
1.750 0.3671 0.00845 0.00226 -0.0284 0.6828 1.0000
2.000 0.3935 0.00861 0.00234 -0.0279 0.6566 1.0000
2.250 0.4199 0.00876 0.00240 -0.0274 0.6299 1.0000
2.500 0.4463 0.00892 0.00247 -0.0269 0.6018 1.0000
2.750 0.4727 0.00911 0.00258 -0.0264 0.5723 1.0000
3.000 0.4990 0.00932 0.00268 -0.0259 0.5412 1.0000
3.250 0.5254 0.00955 0.00281 -0.0254 0.5084 1.0000
3.500 0.5517 0.00980 0.00296 -0.0250 0.4726 1.0000
3.750 0.5779 0.01009 0.00317 -0.0246 0.4341 1.0000
4.000 0.6040 0.01043 0.00338 -0.0242 0.3933 1.0000
4.250 0.6299 0.01083 0.00363 -0.0239 0.3501 1.0000
4.500 0.6557 0.01129 0.00393 -0.0236 0.3069 1.0000
4.750 0.6813 0.01181 0.00432 -0.0233 0.2644 1.0000
5.000 0.7070 0.01238 0.00476 -0.0231 0.2266 1.0000
5.250 0.7324 0.01300 0.00524 -0.0228 0.1946 1.0000
5.500 0.7579 0.01363 0.00579 -0.0225 0.1678 1.0000
5.750 0.7832 0.01431 0.00641 -0.0222 0.1457 1.0000
6.000 0.8083 0.01501 0.00709 -0.0219 0.1259 1.0000
6.250 0.8331 0.01582 0.00788 -0.0215 0.1090 1.0000
6.500 0.8581 0.01656 0.00866 -0.0212 0.0931 1.0000
6.750 0.8826 0.01746 0.00960 -0.0207 0.0797 1.0000
7.000 0.9067 0.01842 0.01061 -0.0203 0.0677 1.0000
7.250 0.9298 0.01968 0.01193 -0.0197 0.0581 1.0000
7.500 0.9535 0.02069 0.01300 -0.0192 0.0496 1.0000
7.750 0.9765 0.02218 0.01469 -0.0184 0.0431 1.0000
8.000 0.9984 0.02380 0.01636 -0.0178 0.0382 1.0000
8.250 1.0198 0.02584 0.01870 -0.0170 0.0341 1.0000
8.500 1.0415 0.02752 0.02063 -0.0162 0.0307 1.0000
8.750 1.0611 0.02969 0.02297 -0.0155 0.0285 1.0000
9.000 1.0727 0.03475 0.02853 -0.0144 0.0269 1.0000
9.250 1.0869 0.03755 0.03185 -0.0134 0.0257 1.0000
9.500 1.0988 0.04049 0.03527 -0.0125 0.0240 1.0000
9.750 1.1019 0.04508 0.04038 -0.0117 0.0235 1.0000
10.000 1.0968 0.05034 0.04613 -0.0112 0.0234 1.0000
10.250 1.0838 0.05586 0.05204 -0.0114 0.0235 1.0000
10.500 1.0639 0.06101 0.05746 -0.0125 0.0237 1.0000
10.750 1.0424 0.06760 0.06425 -0.0179 0.0240 1.0000
11.000 1.0202 0.07636 0.07316 -0.0262 0.0245 1.0000
11.250 0.9955 0.08733 0.08423 -0.0355 0.0252 1.0000
11.500 0.9695 0.09856 0.09542 -0.0427 0.0263 1.0000
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Polar data table (+)
Polar graphs
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