ARA-D 13% AIRFOIL (arad13-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: ARA-D 13% AIRFOIL (arad13-il) Reynolds number: 50,000 Max Cl/Cd: 31.78 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-arad13-il-50000-n5.txt Download as CSV file: xf-arad13-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: ARA-D 13% AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4150 0.10049 0.09327 -0.0185 1.0000 0.0706
-8.750 -0.4183 0.09582 0.08867 -0.0211 1.0000 0.0705
-8.500 -0.4233 0.09121 0.08413 -0.0237 1.0000 0.0707
-8.250 -0.4301 0.08628 0.07926 -0.0270 1.0000 0.0710
-8.000 -0.4344 0.08083 0.07383 -0.0309 1.0000 0.0715
-7.750 -0.4376 0.07512 0.06809 -0.0346 1.0000 0.0720
-7.500 -0.4395 0.06914 0.06202 -0.0380 1.0000 0.0725
-7.250 -0.4393 0.06299 0.05567 -0.0408 1.0000 0.0731
-7.000 -0.4378 0.05626 0.04853 -0.0435 1.0000 0.0748
-6.750 -0.4272 0.05240 0.04445 -0.0441 1.0000 0.0769
-6.500 -0.4133 0.04998 0.04192 -0.0437 1.0000 0.0792
-6.250 -0.4012 0.04622 0.03779 -0.0438 1.0000 0.0820
-6.000 -0.3880 0.04268 0.03378 -0.0436 1.0000 0.0853
-5.750 -0.3736 0.04155 0.03267 -0.0423 1.0000 0.0880
-5.500 -0.3597 0.03947 0.03026 -0.0413 1.0000 0.0917
-5.250 -0.3455 0.03753 0.02797 -0.0402 1.0000 0.0956
-5.000 -0.3157 0.03629 0.02665 -0.0417 0.9940 0.1003
-4.750 -0.2742 0.03414 0.02406 -0.0451 0.9836 0.1073
-4.500 -0.2327 0.03274 0.02242 -0.0482 0.9725 0.1150
-4.250 -0.1911 0.03140 0.02093 -0.0513 0.9616 0.1226
-4.000 -0.1464 0.03004 0.01923 -0.0546 0.9521 0.1325
-3.750 -0.1062 0.02911 0.01827 -0.0571 0.9397 0.1421
-3.500 -0.0671 0.02818 0.01726 -0.0592 0.9267 0.1526
-3.250 -0.0275 0.02734 0.01627 -0.0612 0.9142 0.1652
-3.000 0.0114 0.02664 0.01546 -0.0630 0.9015 0.1794
-2.750 0.0450 0.02604 0.01489 -0.0637 0.8860 0.1935
-2.500 0.0782 0.02550 0.01433 -0.0643 0.8708 0.2096
-2.250 0.1103 0.02500 0.01381 -0.0646 0.8556 0.2281
-2.000 0.1413 0.02451 0.01333 -0.0646 0.8408 0.2496
-1.750 0.1705 0.02404 0.01290 -0.0643 0.8253 0.2754
-1.500 0.1974 0.02354 0.01257 -0.0637 0.8085 0.3090
-1.250 0.2231 0.02290 0.01231 -0.0629 0.7918 0.3702
-1.000 0.2405 0.02156 0.01224 -0.0599 0.7762 0.6171
-0.750 0.2861 0.02085 0.01192 -0.0608 0.7576 1.0000
-0.500 0.3119 0.02096 0.01171 -0.0598 0.7404 1.0000
-0.250 0.3376 0.02108 0.01153 -0.0587 0.7235 1.0000
0.000 0.3634 0.02120 0.01139 -0.0577 0.7066 1.0000
0.250 0.3893 0.02132 0.01128 -0.0568 0.6898 1.0000
0.500 0.4151 0.02149 0.01124 -0.0559 0.6720 1.0000
0.750 0.4409 0.02167 0.01123 -0.0551 0.6541 1.0000
1.000 0.4669 0.02186 0.01123 -0.0543 0.6362 1.0000
1.250 0.4930 0.02206 0.01126 -0.0536 0.6182 1.0000
1.500 0.5192 0.02227 0.01130 -0.0529 0.5999 1.0000
1.750 0.5455 0.02249 0.01137 -0.0522 0.5815 1.0000
2.000 0.5718 0.02273 0.01146 -0.0516 0.5628 1.0000
2.250 0.5979 0.02299 0.01157 -0.0509 0.5441 1.0000
2.500 0.6240 0.02327 0.01171 -0.0503 0.5252 1.0000
2.750 0.6500 0.02358 0.01187 -0.0497 0.5063 1.0000
3.000 0.6759 0.02392 0.01207 -0.0492 0.4875 1.0000
3.250 0.7017 0.02429 0.01231 -0.0486 0.4691 1.0000
3.500 0.7273 0.02470 0.01260 -0.0481 0.4509 1.0000
3.750 0.7528 0.02514 0.01292 -0.0476 0.4333 1.0000
4.000 0.7782 0.02563 0.01330 -0.0471 0.4166 1.0000
4.250 0.8034 0.02616 0.01373 -0.0467 0.4006 1.0000
4.500 0.8284 0.02671 0.01418 -0.0462 0.3856 1.0000
4.750 0.8535 0.02729 0.01464 -0.0457 0.3722 1.0000
5.000 0.8784 0.02789 0.01514 -0.0453 0.3595 1.0000
5.250 0.9028 0.02858 0.01581 -0.0449 0.3466 1.0000
5.500 0.9273 0.02927 0.01642 -0.0444 0.3356 1.0000
5.750 0.9518 0.02996 0.01704 -0.0440 0.3254 1.0000
6.000 0.9757 0.03077 0.01788 -0.0436 0.3151 1.0000
6.250 1.0002 0.03147 0.01844 -0.0431 0.3067 1.0000
6.500 1.0231 0.03240 0.01949 -0.0427 0.2973 1.0000
6.750 1.0475 0.03316 0.02013 -0.0423 0.2900 1.0000
7.000 1.0695 0.03418 0.02127 -0.0418 0.2817 1.0000
7.250 1.0928 0.03503 0.02210 -0.0413 0.2746 1.0000
7.500 1.1150 0.03607 0.02319 -0.0408 0.2680 1.0000
7.750 1.1359 0.03716 0.02438 -0.0402 0.2611 1.0000
8.000 1.1600 0.03798 0.02511 -0.0398 0.2556 1.0000
8.250 1.1776 0.03939 0.02674 -0.0390 0.2492 1.0000
8.500 1.1973 0.04056 0.02800 -0.0383 0.2434 1.0000
8.750 1.2214 0.04143 0.02876 -0.0379 0.2388 1.0000
9.000 1.2339 0.04318 0.03083 -0.0367 0.2330 1.0000
9.250 1.2500 0.04461 0.03239 -0.0357 0.2279 1.0000
9.500 1.2714 0.04563 0.03338 -0.0352 0.2237 1.0000
9.750 1.2831 0.04743 0.03539 -0.0339 0.2192 1.0000
10.000 1.2891 0.04955 0.03777 -0.0323 0.2145 1.0000
10.250 1.3020 0.05110 0.03942 -0.0311 0.2104 1.0000
10.500 1.3244 0.05206 0.04032 -0.0306 0.2070 1.0000
10.750 1.3177 0.05500 0.04360 -0.0282 0.2035 1.0000
11.000 1.3015 0.05835 0.04727 -0.0253 0.2001 1.0000
11.250 1.2870 0.06159 0.05072 -0.0228 0.1972 1.0000
11.500 1.2882 0.06395 0.05316 -0.0215 0.1942 1.0000
11.750 1.3197 0.06412 0.05322 -0.0212 0.1912 1.0000
12.000 1.2498 0.07328 0.06284 -0.0204 0.1894 1.0000
12.250 0.9906 0.12053 0.11066 -0.0435 0.1792 1.0000
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Polar data table (+)
Polar graphs
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