AG03 (flat aft bottom) (ag03-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG03 (flat aft bottom) (ag03-il) Reynolds number: 500,000 Max Cl/Cd: 74.72 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag03-il-500000-n5.txt Download as CSV file: xf-ag03-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5766 0.12798 0.12567 0.0273 1.0000 0.0068
-10.000 -0.5718 0.12404 0.12174 0.0254 1.0000 0.0070
-8.750 -0.5503 0.10462 0.10240 0.0161 1.0000 0.0072
-7.500 -0.4522 0.06724 0.06522 -0.0037 1.0000 0.0045
-7.250 -0.4544 0.06272 0.06074 -0.0062 1.0000 0.0044
-6.750 -0.5039 0.06615 0.06396 -0.0140 1.0000 0.0042
-6.500 -0.4874 0.05994 0.05769 -0.0200 1.0000 0.0042
-6.250 -0.4683 0.05335 0.05099 -0.0254 1.0000 0.0042
-6.000 -0.4474 0.04583 0.04328 -0.0300 1.0000 0.0044
-5.750 -0.4275 0.03817 0.03533 -0.0333 1.0000 0.0045
-5.500 -0.4064 0.03152 0.02832 -0.0347 1.0000 0.0046
-5.250 -0.3847 0.02631 0.02272 -0.0350 1.0000 0.0048
-5.000 -0.3614 0.02477 0.02101 -0.0349 1.0000 0.0053
-4.750 -0.3381 0.02190 0.01780 -0.0345 1.0000 0.0059
-4.500 -0.3145 0.01873 0.01417 -0.0337 1.0000 0.0061
-4.250 -0.2905 0.01605 0.01104 -0.0328 1.0000 0.0059
-4.000 -0.2606 0.01399 0.00860 -0.0330 0.9971 0.0057
-3.750 -0.2270 0.01245 0.00677 -0.0341 0.9911 0.0056
-3.500 -0.1930 0.01130 0.00541 -0.0352 0.9834 0.0056
-3.250 -0.1597 0.01043 0.00442 -0.0362 0.9732 0.0057
-3.000 -0.1264 0.00975 0.00364 -0.0373 0.9607 0.0058
-2.750 -0.0942 0.00924 0.00303 -0.0380 0.9451 0.0060
-2.500 -0.0645 0.00886 0.00254 -0.0381 0.9256 0.0065
-2.250 -0.0371 0.00860 0.00214 -0.0376 0.9021 0.0074
-2.000 -0.0109 0.00830 0.00178 -0.0369 0.8767 0.0167
-1.750 0.0149 0.00803 0.00158 -0.0363 0.8494 0.0527
-1.500 0.0406 0.00775 0.00144 -0.0358 0.8208 0.1147
-1.250 0.0667 0.00760 0.00131 -0.0353 0.7910 0.1619
-1.000 0.0930 0.00744 0.00120 -0.0350 0.7614 0.2218
-0.750 0.1192 0.00716 0.00112 -0.0347 0.7324 0.3271
-0.500 0.1447 0.00670 0.00106 -0.0344 0.7035 0.4989
-0.250 0.1686 0.00615 0.00103 -0.0337 0.6755 0.6971
0.000 0.1882 0.00570 0.00105 -0.0314 0.6487 0.8729
0.250 0.2274 0.00569 0.00101 -0.0335 0.6166 0.9935
0.500 0.2560 0.00583 0.00098 -0.0336 0.5869 1.0000
0.750 0.2829 0.00599 0.00098 -0.0333 0.5570 1.0000
1.000 0.3098 0.00616 0.00099 -0.0331 0.5265 1.0000
1.250 0.3368 0.00633 0.00101 -0.0329 0.4963 1.0000
1.500 0.3638 0.00652 0.00105 -0.0327 0.4662 1.0000
1.750 0.3908 0.00671 0.00112 -0.0325 0.4361 1.0000
2.000 0.4178 0.00692 0.00118 -0.0324 0.4065 1.0000
2.250 0.4448 0.00712 0.00126 -0.0322 0.3784 1.0000
2.500 0.4718 0.00733 0.00136 -0.0321 0.3522 1.0000
2.750 0.4988 0.00755 0.00147 -0.0320 0.3255 1.0000
3.000 0.5258 0.00779 0.00161 -0.0318 0.2994 1.0000
3.250 0.5527 0.00803 0.00175 -0.0317 0.2741 1.0000
3.500 0.5795 0.00828 0.00190 -0.0316 0.2492 1.0000
3.750 0.6064 0.00854 0.00206 -0.0315 0.2252 1.0000
4.000 0.6332 0.00880 0.00227 -0.0313 0.2046 1.0000
4.250 0.6600 0.00907 0.00247 -0.0312 0.1848 1.0000
4.500 0.6867 0.00936 0.00268 -0.0311 0.1640 1.0000
4.750 0.7134 0.00964 0.00292 -0.0309 0.1472 1.0000
5.000 0.7399 0.00995 0.00319 -0.0308 0.1300 1.0000
5.250 0.7663 0.01029 0.00347 -0.0306 0.1122 1.0000
5.500 0.7927 0.01061 0.00376 -0.0305 0.0983 1.0000
5.750 0.8189 0.01096 0.00409 -0.0303 0.0847 1.0000
6.000 0.8450 0.01134 0.00444 -0.0301 0.0715 1.0000
6.250 0.8710 0.01172 0.00483 -0.0299 0.0621 1.0000
6.500 0.8968 0.01215 0.00524 -0.0297 0.0526 1.0000
6.750 0.9227 0.01252 0.00564 -0.0295 0.0459 1.0000
7.000 0.9484 0.01296 0.00611 -0.0292 0.0398 1.0000
7.250 0.9739 0.01339 0.00656 -0.0290 0.0341 1.0000
7.500 0.9991 0.01387 0.00711 -0.0287 0.0292 1.0000
7.750 1.0243 0.01434 0.00762 -0.0284 0.0247 1.0000
8.000 1.0489 0.01493 0.00825 -0.0281 0.0205 1.0000
8.250 1.0737 0.01542 0.00882 -0.0278 0.0175 1.0000
8.500 1.0974 0.01615 0.00957 -0.0274 0.0137 1.0000
8.750 1.1217 0.01671 0.01024 -0.0270 0.0121 1.0000
9.000 1.1451 0.01741 0.01100 -0.0266 0.0099 1.0000
9.250 1.1679 0.01821 0.01192 -0.0261 0.0079 1.0000
9.500 1.1909 0.01890 0.01268 -0.0256 0.0063 1.0000
9.750 1.2124 0.01983 0.01369 -0.0251 0.0049 1.0000
10.000 1.2346 0.02060 0.01457 -0.0246 0.0039 1.0000
10.250 1.2552 0.02159 0.01567 -0.0239 0.0032 1.0000
10.500 1.2746 0.02276 0.01700 -0.0232 0.0027 1.0000
10.750 1.2938 0.02387 0.01828 -0.0224 0.0023 1.0000
11.000 1.3119 0.02508 0.01965 -0.0216 0.0020 1.0000
11.250 1.3286 0.02641 0.02115 -0.0206 0.0017 1.0000
11.500 1.3416 0.02815 0.02313 -0.0195 0.0015 1.0000
11.750 1.3523 0.03005 0.02525 -0.0182 0.0014 1.0000
12.000 1.3622 0.03184 0.02726 -0.0169 0.0013 1.0000
12.250 1.3681 0.03388 0.02952 -0.0154 0.0012 1.0000
12.500 1.3678 0.03607 0.03192 -0.0134 0.0011 1.0000
12.750 1.3623 0.03869 0.03474 -0.0118 0.0011 1.0000
13.000 1.3539 0.04208 0.03834 -0.0116 0.0010 1.0000
13.250 1.3433 0.04658 0.04305 -0.0134 0.0010 1.0000
13.500 1.3292 0.05268 0.04936 -0.0173 0.0010 1.0000
13.750 1.3111 0.06060 0.05751 -0.0232 0.0010 1.0000
14.000 1.2872 0.07039 0.06749 -0.0300 0.0010 1.0000
14.250 1.2577 0.08127 0.07853 -0.0365 0.0011 1.0000
14.500 1.2250 0.09253 0.08992 -0.0425 0.0012 1.0000
14.750 1.1900 0.10415 0.10165 -0.0483 0.0012 1.0000
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Polar data table (+)
Polar graphs
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