AG36 (ag36-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG36 (ag36-il) Reynolds number: 500,000 Max Cl/Cd: 88.94 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag36-il-500000.txt Download as CSV file: xf-ag36-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG36
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5131 0.08796 0.08578 -0.0066 1.0000 0.0197
-9.500 -0.5120 0.08369 0.08153 -0.0096 1.0000 0.0202
-9.250 -0.5118 0.07903 0.07691 -0.0139 1.0000 0.0207
-9.000 -0.5049 0.07240 0.07028 -0.0226 1.0000 0.0216
-8.750 -0.4887 0.06397 0.06175 -0.0334 1.0000 0.0224
-8.500 -0.4775 0.05676 0.05437 -0.0388 1.0000 0.0225
-8.250 -0.4534 0.03346 0.03103 -0.0423 1.0000 0.0234
-8.000 -0.4447 0.03095 0.02851 -0.0415 1.0000 0.0238
-7.750 -0.4358 0.02831 0.02579 -0.0407 1.0000 0.0244
-7.500 -0.4264 0.02583 0.02322 -0.0397 1.0000 0.0253
-7.250 -0.4177 0.02277 0.01998 -0.0386 1.0000 0.0262
-7.000 -0.4024 0.01939 0.01629 -0.0383 0.9993 0.0284
-6.750 -0.3976 0.02422 0.01987 -0.0387 1.0000 0.0220
-6.500 -0.3812 0.01946 0.01456 -0.0373 1.0000 0.0201
-6.250 -0.3483 0.01643 0.01105 -0.0383 0.9981 0.0198
-6.000 -0.3122 0.01480 0.00916 -0.0399 0.9957 0.0205
-5.750 -0.2760 0.01360 0.00779 -0.0415 0.9930 0.0213
-5.500 -0.2396 0.01292 0.00698 -0.0431 0.9892 0.0224
-5.250 -0.2041 0.01142 0.00539 -0.0448 0.9861 0.0246
-5.000 -0.1656 0.01075 0.00470 -0.0470 0.9833 0.0267
-4.750 -0.1316 0.01023 0.00413 -0.0482 0.9767 0.0292
-4.500 -0.0961 0.00954 0.00339 -0.0497 0.9709 0.0335
-4.250 -0.0645 0.00921 0.00306 -0.0503 0.9611 0.0391
-4.000 -0.0336 0.00876 0.00260 -0.0507 0.9504 0.0496
-3.750 -0.0052 0.00829 0.00226 -0.0506 0.9368 0.0850
-3.500 0.0209 0.00778 0.00205 -0.0501 0.9196 0.1712
-3.250 0.0462 0.00731 0.00190 -0.0496 0.9002 0.2774
-3.000 0.0715 0.00690 0.00177 -0.0490 0.8788 0.3817
-2.750 0.0960 0.00638 0.00167 -0.0482 0.8585 0.5311
-2.500 0.1177 0.00570 0.00165 -0.0467 0.8388 0.7446
-2.250 0.1358 0.00529 0.00168 -0.0435 0.8191 0.9256
-2.000 0.1863 0.00530 0.00158 -0.0481 0.7981 0.9995
-1.750 0.2127 0.00539 0.00151 -0.0476 0.7752 1.0000
-1.500 0.2387 0.00549 0.00146 -0.0471 0.7503 1.0000
-1.250 0.2649 0.00560 0.00141 -0.0466 0.7216 1.0000
-1.000 0.2911 0.00572 0.00137 -0.0461 0.6851 1.0000
-0.750 0.3171 0.00590 0.00132 -0.0457 0.6422 1.0000
-0.500 0.3434 0.00610 0.00133 -0.0453 0.6152 1.0000
-0.250 0.3701 0.00629 0.00138 -0.0451 0.5962 1.0000
0.000 0.3972 0.00646 0.00144 -0.0449 0.5806 1.0000
0.250 0.4245 0.00661 0.00150 -0.0448 0.5664 1.0000
0.500 0.4519 0.00674 0.00158 -0.0447 0.5532 1.0000
0.750 0.4794 0.00687 0.00165 -0.0446 0.5406 1.0000
1.000 0.5069 0.00699 0.00173 -0.0446 0.5280 1.0000
1.250 0.5344 0.00712 0.00181 -0.0445 0.5152 1.0000
1.500 0.5620 0.00725 0.00191 -0.0445 0.5021 1.0000
1.750 0.5895 0.00737 0.00201 -0.0444 0.4883 1.0000
2.000 0.6170 0.00749 0.00210 -0.0444 0.4727 1.0000
2.250 0.6446 0.00762 0.00220 -0.0444 0.4543 1.0000
2.500 0.6718 0.00778 0.00231 -0.0444 0.4348 1.0000
2.750 0.6989 0.00796 0.00244 -0.0443 0.4113 1.0000
3.000 0.7258 0.00819 0.00259 -0.0443 0.3863 1.0000
3.250 0.7524 0.00846 0.00278 -0.0442 0.3584 1.0000
3.500 0.7788 0.00877 0.00299 -0.0441 0.3299 1.0000
3.750 0.8051 0.00910 0.00322 -0.0440 0.3030 1.0000
4.000 0.8312 0.00945 0.00348 -0.0439 0.2743 1.0000
4.250 0.8570 0.00985 0.00378 -0.0438 0.2417 1.0000
4.500 0.8823 0.01032 0.00409 -0.0437 0.2086 1.0000
4.750 0.9077 0.01078 0.00444 -0.0435 0.1800 1.0000
5.000 0.9330 0.01124 0.00481 -0.0434 0.1541 1.0000
5.250 0.9582 0.01172 0.00521 -0.0433 0.1302 1.0000
5.500 0.9830 0.01223 0.00563 -0.0431 0.1075 1.0000
5.750 1.0073 0.01280 0.00610 -0.0428 0.0848 1.0000
6.000 1.0310 0.01347 0.00664 -0.0425 0.0605 1.0000
6.250 1.0536 0.01431 0.00736 -0.0420 0.0378 1.0000
6.500 1.0760 0.01515 0.00818 -0.0414 0.0264 1.0000
6.750 1.0980 0.01606 0.00913 -0.0408 0.0209 1.0000
7.000 1.1194 0.01700 0.01010 -0.0400 0.0174 1.0000
7.250 1.1408 0.01787 0.01108 -0.0393 0.0154 1.0000
7.500 1.1623 0.01867 0.01197 -0.0387 0.0140 1.0000
7.750 1.1810 0.01982 0.01318 -0.0377 0.0128 1.0000
8.000 1.1949 0.02153 0.01504 -0.0360 0.0119 1.0000
8.250 1.2138 0.02253 0.01616 -0.0350 0.0115 1.0000
8.500 1.2310 0.02371 0.01747 -0.0338 0.0110 1.0000
8.750 1.2467 0.02501 0.01889 -0.0325 0.0105 1.0000
9.000 1.2613 0.02639 0.02039 -0.0311 0.0101 1.0000
9.250 1.2744 0.02785 0.02199 -0.0296 0.0098 1.0000
9.500 1.2857 0.02944 0.02370 -0.0280 0.0095 1.0000
9.750 1.2945 0.03122 0.02561 -0.0261 0.0093 1.0000
10.000 1.2986 0.03313 0.02766 -0.0237 0.0091 1.0000
10.250 1.2990 0.03545 0.03013 -0.0211 0.0090 1.0000
10.500 1.2952 0.03839 0.03327 -0.0187 0.0088 1.0000
10.750 1.2866 0.04203 0.03715 -0.0165 0.0087 1.0000
11.000 1.2769 0.04563 0.04099 -0.0152 0.0086 1.0000
11.250 1.2721 0.04854 0.04411 -0.0149 0.0085 1.0000
11.500 1.2650 0.05214 0.04790 -0.0153 0.0085 1.0000
11.750 1.2552 0.05648 0.05244 -0.0165 0.0085 1.0000
12.000 1.2428 0.06155 0.05772 -0.0184 0.0085 1.0000
12.250 1.2284 0.06737 0.06373 -0.0211 0.0085 1.0000
12.500 1.2119 0.07383 0.07037 -0.0243 0.0085 1.0000
12.750 1.1935 0.08083 0.07755 -0.0280 0.0085 1.0000
13.000 1.1731 0.08846 0.08534 -0.0320 0.0086 1.0000
13.250 1.0281 0.08577 0.08269 -0.0176 0.0089 1.0000
13.500 1.0081 0.09272 0.08979 -0.0204 0.0090 1.0000
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Polar data table (+)
Polar graphs
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