AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.31 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag03-il-1000000.txt Download as CSV file: xf-ag03-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: AG03 (flat aft bottom)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4365 0.08388 0.08241 0.0033 1.0000 0.0059
-8.000 -0.4366 0.07968 0.07822 0.0020 1.0000 0.0061
-7.750 -0.4374 0.07536 0.07392 0.0006 1.0000 0.0063
-7.500 -0.4387 0.07111 0.06967 -0.0010 1.0000 0.0063
-7.250 -0.4410 0.06673 0.06531 -0.0030 1.0000 0.0065
-7.000 -0.4433 0.06194 0.06054 -0.0066 1.0000 0.0067
-6.750 -0.4372 0.05616 0.05476 -0.0126 1.0000 0.0070
-6.500 -0.4287 0.05056 0.04913 -0.0178 1.0000 0.0071
-6.250 -0.4164 0.04472 0.04324 -0.0226 1.0000 0.0072
-6.000 -0.4027 0.03880 0.03724 -0.0266 1.0000 0.0072
-5.750 -0.3876 0.03285 0.03117 -0.0298 1.0000 0.0072
-5.500 -0.3715 0.02701 0.02517 -0.0319 1.0000 0.0073
-5.250 -0.3635 0.01674 0.01447 -0.0340 1.0000 0.0076
-3.250 -0.1650 0.01028 0.00554 -0.0357 0.9901 0.0090
-3.000 -0.1299 0.00912 0.00418 -0.0367 0.9842 0.0076
-2.750 -0.0964 0.00859 0.00360 -0.0377 0.9748 0.0074
-2.500 -0.0644 0.00787 0.00278 -0.0384 0.9621 0.0072
-2.250 -0.0356 0.00736 0.00215 -0.0382 0.9448 0.0073
-2.000 -0.0092 0.00695 0.00160 -0.0375 0.9238 0.0078
-1.750 0.0165 0.00652 0.00120 -0.0367 0.9005 0.0441
-1.500 0.0423 0.00628 0.00107 -0.0361 0.8752 0.0975
-1.250 0.0685 0.00613 0.00097 -0.0356 0.8479 0.1465
-1.000 0.0945 0.00580 0.00089 -0.0353 0.8193 0.2577
-0.750 0.1194 0.00509 0.00083 -0.0350 0.7898 0.5081
-0.500 0.1429 0.00440 0.00081 -0.0342 0.7612 0.7568
-0.250 0.1619 0.00400 0.00082 -0.0317 0.7335 0.9306
0.000 0.2035 0.00405 0.00077 -0.0346 0.7016 1.0000
0.250 0.2305 0.00418 0.00075 -0.0343 0.6718 1.0000
0.500 0.2575 0.00431 0.00074 -0.0340 0.6422 1.0000
0.750 0.2847 0.00445 0.00073 -0.0338 0.6126 1.0000
1.000 0.3118 0.00461 0.00074 -0.0336 0.5820 1.0000
1.250 0.3391 0.00476 0.00077 -0.0334 0.5511 1.0000
1.500 0.3663 0.00492 0.00080 -0.0333 0.5190 1.0000
1.750 0.3935 0.00510 0.00085 -0.0331 0.4869 1.0000
2.000 0.4208 0.00529 0.00090 -0.0330 0.4560 1.0000
2.250 0.4480 0.00548 0.00096 -0.0329 0.4237 1.0000
2.500 0.4752 0.00569 0.00104 -0.0328 0.3915 1.0000
2.750 0.5024 0.00590 0.00113 -0.0327 0.3616 1.0000
3.000 0.5296 0.00612 0.00124 -0.0326 0.3315 1.0000
3.250 0.5567 0.00635 0.00135 -0.0325 0.3026 1.0000
3.500 0.5839 0.00657 0.00148 -0.0324 0.2778 1.0000
3.750 0.6111 0.00680 0.00161 -0.0323 0.2528 1.0000
4.000 0.6381 0.00704 0.00177 -0.0322 0.2279 1.0000
4.250 0.6652 0.00728 0.00193 -0.0321 0.2074 1.0000
4.500 0.6922 0.00753 0.00210 -0.0320 0.1857 1.0000
4.750 0.7190 0.00780 0.00230 -0.0319 0.1640 1.0000
5.000 0.7459 0.00808 0.00251 -0.0318 0.1453 1.0000
5.250 0.7726 0.00837 0.00274 -0.0317 0.1268 1.0000
5.500 0.7992 0.00868 0.00298 -0.0316 0.1080 1.0000
5.750 0.8257 0.00902 0.00325 -0.0314 0.0917 1.0000
6.000 0.8520 0.00937 0.00356 -0.0313 0.0763 1.0000
6.250 0.8784 0.00972 0.00387 -0.0311 0.0639 1.0000
6.500 0.9046 0.01010 0.00421 -0.0309 0.0539 1.0000
6.750 0.9309 0.01041 0.00453 -0.0308 0.0471 1.0000
7.000 0.9570 0.01080 0.00492 -0.0306 0.0399 1.0000
7.250 0.9829 0.01118 0.00528 -0.0304 0.0340 1.0000
7.500 1.0088 0.01157 0.00572 -0.0302 0.0290 1.0000
7.750 1.0344 0.01199 0.00613 -0.0299 0.0238 1.0000
8.000 1.0599 0.01241 0.00659 -0.0297 0.0198 1.0000
8.250 1.0850 0.01290 0.00705 -0.0294 0.0155 1.0000
8.500 1.1101 0.01336 0.00756 -0.0292 0.0126 1.0000
8.750 1.1348 0.01390 0.00810 -0.0289 0.0099 1.0000
9.000 1.1590 0.01453 0.00880 -0.0285 0.0080 1.0000
9.250 1.1833 0.01507 0.00941 -0.0281 0.0066 1.0000
9.500 1.2059 0.01598 0.01040 -0.0276 0.0049 1.0000
9.750 1.2299 0.01653 0.01102 -0.0272 0.0041 1.0000
10.000 1.2502 0.01779 0.01240 -0.0264 0.0028 1.0000
10.250 1.2732 0.01846 0.01316 -0.0259 0.0023 1.0000
10.500 1.2947 0.01933 0.01412 -0.0254 0.0018 1.0000
10.750 1.3085 0.02155 0.01662 -0.0239 0.0014 1.0000
11.000 1.3273 0.02273 0.01795 -0.0230 0.0013 1.0000
11.250 1.3435 0.02421 0.01965 -0.0220 0.0012 1.0000
11.500 1.3573 0.02593 0.02158 -0.0207 0.0011 1.0000
11.750 1.3682 0.02788 0.02375 -0.0193 0.0011 1.0000
12.000 1.3756 0.03005 0.02615 -0.0177 0.0011 1.0000
12.250 1.3785 0.03247 0.02880 -0.0159 0.0010 1.0000
12.500 1.3737 0.03500 0.03155 -0.0135 0.0010 1.0000
12.750 1.3637 0.03800 0.03474 -0.0118 0.0010 1.0000
13.000 1.3511 0.04206 0.03902 -0.0122 0.0010 1.0000
13.250 1.3367 0.04762 0.04478 -0.0153 0.0010 1.0000
13.500 1.3202 0.05492 0.05228 -0.0207 0.0010 1.0000
13.750 1.3007 0.06375 0.06129 -0.0272 0.0010 1.0000
14.000 1.2774 0.07355 0.07126 -0.0337 0.0011 1.0000
14.250 1.2522 0.08339 0.08121 -0.0392 0.0011 1.0000
14.500 1.2254 0.09327 0.09120 -0.0443 0.0011 1.0000
14.750 1.1981 0.10315 0.10116 -0.0490 0.0011 1.0000
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Polar data table (+)
Polar graphs
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