AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 500,000 Max Cl/Cd: 81.14 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag27-il-500000-n5.txt Download as CSV file: xf-ag27-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG27 Bubble Dancer DLG by Mark Drela
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4978 0.09298 0.09079 0.0051 1.0000 0.0058
-7.750 -0.4936 0.08901 0.08684 0.0027 1.0000 0.0059
-7.500 -0.4893 0.08501 0.08287 0.0000 1.0000 0.0059
-7.250 -0.4814 0.08054 0.07842 -0.0042 1.0000 0.0060
-7.000 -0.4695 0.07557 0.07346 -0.0098 1.0000 0.0060
-6.750 -0.4543 0.07000 0.06790 -0.0167 1.0000 0.0062
-6.500 -0.4337 0.06330 0.06117 -0.0251 1.0000 0.0068
-5.750 -0.3581 0.04106 0.03857 -0.0495 1.0000 0.0066
-5.500 -0.3304 0.03146 0.02854 -0.0556 1.0000 0.0063
-5.250 -0.3031 0.02155 0.01777 -0.0593 1.0000 0.0060
-5.000 -0.2765 0.01703 0.01253 -0.0600 1.0000 0.0060
-4.750 -0.2453 0.01453 0.00951 -0.0609 0.9978 0.0061
-4.500 -0.2106 0.01286 0.00750 -0.0625 0.9942 0.0064
-4.250 -0.1775 0.01176 0.00618 -0.0636 0.9884 0.0068
-4.000 -0.1433 0.01067 0.00491 -0.0650 0.9829 0.0074
-3.750 -0.1108 0.01005 0.00422 -0.0660 0.9745 0.0083
-3.500 -0.0778 0.00961 0.00370 -0.0670 0.9653 0.0093
-3.250 -0.0457 0.00931 0.00334 -0.0677 0.9536 0.0108
-3.000 -0.0151 0.00875 0.00269 -0.0681 0.9391 0.0128
-2.750 0.0136 0.00846 0.00233 -0.0680 0.9218 0.0156
-2.500 0.0410 0.00819 0.00200 -0.0676 0.9030 0.0219
-2.250 0.0677 0.00799 0.00176 -0.0671 0.8836 0.0344
-2.000 0.0944 0.00781 0.00157 -0.0667 0.8629 0.0541
-1.750 0.1212 0.00763 0.00142 -0.0663 0.8422 0.0872
-1.500 0.1481 0.00746 0.00129 -0.0659 0.8205 0.1299
-1.250 0.1750 0.00729 0.00119 -0.0657 0.7983 0.1829
-1.000 0.2021 0.00716 0.00111 -0.0654 0.7752 0.2382
-0.750 0.2292 0.00704 0.00106 -0.0652 0.7512 0.2986
-0.500 0.2563 0.00693 0.00104 -0.0650 0.7268 0.3634
-0.250 0.2835 0.00684 0.00102 -0.0648 0.7018 0.4294
0.000 0.3106 0.00676 0.00102 -0.0646 0.6757 0.5002
0.250 0.3373 0.00661 0.00104 -0.0643 0.6483 0.5958
0.500 0.3604 0.00610 0.00107 -0.0632 0.6212 0.8034
0.750 0.3872 0.00591 0.00103 -0.0625 0.5921 1.0000
1.000 0.4147 0.00609 0.00105 -0.0623 0.5624 1.0000
1.250 0.4421 0.00628 0.00109 -0.0622 0.5318 1.0000
1.500 0.4694 0.00648 0.00114 -0.0620 0.5003 1.0000
1.750 0.4968 0.00669 0.00121 -0.0619 0.4697 1.0000
2.000 0.5241 0.00691 0.00128 -0.0617 0.4389 1.0000
2.250 0.5513 0.00715 0.00138 -0.0616 0.4077 1.0000
2.500 0.5785 0.00740 0.00149 -0.0614 0.3757 1.0000
2.750 0.6056 0.00767 0.00163 -0.0613 0.3439 1.0000
3.000 0.6326 0.00795 0.00178 -0.0612 0.3117 1.0000
3.250 0.6596 0.00823 0.00193 -0.0610 0.2832 1.0000
3.500 0.6865 0.00853 0.00211 -0.0609 0.2525 1.0000
3.750 0.7133 0.00884 0.00233 -0.0608 0.2255 1.0000
4.000 0.7401 0.00915 0.00254 -0.0606 0.2008 1.0000
4.250 0.7667 0.00949 0.00277 -0.0605 0.1760 1.0000
4.500 0.7935 0.00978 0.00301 -0.0603 0.1579 1.0000
4.750 0.8201 0.01011 0.00329 -0.0601 0.1398 1.0000
5.000 0.8466 0.01045 0.00357 -0.0599 0.1231 1.0000
5.250 0.8731 0.01078 0.00386 -0.0598 0.1102 1.0000
5.500 0.8994 0.01112 0.00417 -0.0595 0.0967 1.0000
5.750 0.9257 0.01147 0.00450 -0.0593 0.0854 1.0000
6.000 0.9519 0.01183 0.00487 -0.0591 0.0745 1.0000
6.250 0.9780 0.01219 0.00524 -0.0588 0.0656 1.0000
6.500 1.0038 0.01260 0.00564 -0.0586 0.0567 1.0000
6.750 1.0293 0.01305 0.00607 -0.0583 0.0471 1.0000
7.000 1.0547 0.01351 0.00653 -0.0580 0.0387 1.0000
7.250 1.0800 0.01397 0.00703 -0.0577 0.0317 1.0000
7.500 1.1048 0.01452 0.00758 -0.0573 0.0249 1.0000
7.750 1.1292 0.01513 0.00819 -0.0569 0.0186 1.0000
8.000 1.1536 0.01571 0.00881 -0.0565 0.0144 1.0000
8.250 1.1774 0.01640 0.00954 -0.0560 0.0111 1.0000
8.500 1.2012 0.01707 0.01029 -0.0555 0.0090 1.0000
8.750 1.2237 0.01798 0.01131 -0.0548 0.0072 1.0000
9.000 1.2469 0.01869 0.01213 -0.0542 0.0062 1.0000
9.250 1.2693 0.01948 0.01300 -0.0536 0.0053 1.0000
9.500 1.2896 0.02067 0.01432 -0.0528 0.0044 1.0000
9.750 1.3109 0.02159 0.01538 -0.0521 0.0041 1.0000
10.000 1.3312 0.02263 0.01658 -0.0512 0.0038 1.0000
10.250 1.3505 0.02375 0.01786 -0.0503 0.0035 1.0000
10.500 1.3689 0.02495 0.01921 -0.0493 0.0033 1.0000
10.750 1.3862 0.02621 0.02063 -0.0483 0.0030 1.0000
11.000 1.4018 0.02763 0.02224 -0.0471 0.0029 1.0000
11.250 1.4139 0.02939 0.02419 -0.0457 0.0027 1.0000
11.500 1.4191 0.03182 0.02686 -0.0437 0.0025 1.0000
11.750 1.4233 0.03409 0.02936 -0.0417 0.0024 1.0000
12.000 1.4251 0.03615 0.03162 -0.0395 0.0024 1.0000
12.250 1.4216 0.03845 0.03412 -0.0371 0.0024 1.0000
12.500 1.4150 0.04130 0.03717 -0.0356 0.0023 1.0000
12.750 1.4065 0.04486 0.04094 -0.0354 0.0023 1.0000
13.000 1.3956 0.04938 0.04568 -0.0366 0.0023 1.0000
13.250 1.3829 0.05493 0.05143 -0.0393 0.0023 1.0000
13.500 1.3678 0.06168 0.05839 -0.0434 0.0023 1.0000
13.750 1.3495 0.06966 0.06656 -0.0485 0.0023 1.0000
14.000 1.3285 0.07862 0.07570 -0.0541 0.0023 1.0000
14.250 1.3048 0.08827 0.08549 -0.0596 0.0023 1.0000
14.500 1.2792 0.09831 0.09566 -0.0650 0.0024 1.0000
14.750 1.2528 0.10849 0.10594 -0.0701 0.0024 1.0000
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Polar data table (+)
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