AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 500,000 Max Cl/Cd: 92.08 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag24-il-500000.txt Download as CSV file: xf-ag24-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: AG24 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4010 0.08850 0.08642 -0.0157 1.0000 0.0168
-9.000 -0.4181 0.08031 0.07828 -0.0178 1.0000 0.0174
-8.750 -0.4206 0.07570 0.07368 -0.0191 1.0000 0.0178
-8.500 -0.4198 0.07197 0.06997 -0.0201 1.0000 0.0181
-8.250 -0.4199 0.06808 0.06610 -0.0214 1.0000 0.0185
-8.000 -0.4225 0.06355 0.06160 -0.0233 1.0000 0.0188
-7.750 -0.4271 0.05869 0.05676 -0.0258 1.0000 0.0190
-7.500 -0.4341 0.05320 0.05131 -0.0300 1.0000 0.0192
-5.500 -0.3869 0.01864 0.01381 -0.0524 0.9994 0.0140
-5.250 -0.3508 0.01554 0.01024 -0.0542 0.9974 0.0134
-5.000 -0.3141 0.01392 0.00840 -0.0561 0.9953 0.0140
-4.750 -0.2773 0.01278 0.00709 -0.0579 0.9929 0.0153
-4.500 -0.2409 0.01200 0.00620 -0.0597 0.9894 0.0165
-4.250 -0.2041 0.01070 0.00481 -0.0618 0.9864 0.0199
-4.000 -0.1653 0.01013 0.00418 -0.0641 0.9838 0.0238
-3.750 -0.1277 0.00938 0.00337 -0.0662 0.9804 0.0319
-3.500 -0.0929 0.00878 0.00284 -0.0676 0.9745 0.0595
-3.250 -0.0574 0.00813 0.00250 -0.0695 0.9696 0.1347
-3.000 -0.0271 0.00768 0.00230 -0.0702 0.9606 0.2085
-2.750 0.0030 0.00730 0.00214 -0.0706 0.9517 0.2789
-2.500 0.0310 0.00699 0.00200 -0.0706 0.9414 0.3433
-2.250 0.0574 0.00672 0.00189 -0.0701 0.9290 0.4049
-2.000 0.0836 0.00650 0.00180 -0.0696 0.9161 0.4608
-1.750 0.1099 0.00631 0.00172 -0.0690 0.9027 0.5133
-1.500 0.1361 0.00612 0.00165 -0.0685 0.8887 0.5686
-1.250 0.1623 0.00597 0.00160 -0.0679 0.8740 0.6227
-1.000 0.1884 0.00582 0.00156 -0.0672 0.8588 0.6777
-0.750 0.2142 0.00569 0.00154 -0.0665 0.8431 0.7338
-0.500 0.2395 0.00558 0.00153 -0.0656 0.8262 0.7894
-0.250 0.2637 0.00548 0.00152 -0.0644 0.8086 0.8429
0.000 0.2859 0.00539 0.00149 -0.0626 0.7907 0.8973
0.250 0.3150 0.00528 0.00138 -0.0623 0.7718 0.9861
0.500 0.3438 0.00536 0.00135 -0.0624 0.7513 1.0000
0.750 0.3717 0.00547 0.00134 -0.0623 0.7305 1.0000
1.000 0.3996 0.00559 0.00134 -0.0623 0.7081 1.0000
1.250 0.4274 0.00572 0.00137 -0.0622 0.6852 1.0000
1.500 0.4552 0.00587 0.00139 -0.0621 0.6615 1.0000
1.750 0.4829 0.00602 0.00144 -0.0620 0.6369 1.0000
2.000 0.5106 0.00619 0.00149 -0.0619 0.6113 1.0000
2.250 0.5382 0.00637 0.00158 -0.0618 0.5857 1.0000
2.500 0.5657 0.00656 0.00166 -0.0617 0.5602 1.0000
2.750 0.5932 0.00676 0.00176 -0.0617 0.5342 1.0000
3.000 0.6206 0.00698 0.00187 -0.0616 0.5080 1.0000
3.250 0.6480 0.00720 0.00202 -0.0615 0.4816 1.0000
3.500 0.6753 0.00744 0.00216 -0.0614 0.4553 1.0000
3.750 0.7025 0.00768 0.00232 -0.0613 0.4289 1.0000
4.000 0.7297 0.00794 0.00249 -0.0613 0.4025 1.0000
4.250 0.7567 0.00822 0.00270 -0.0612 0.3754 1.0000
4.500 0.7836 0.00851 0.00291 -0.0611 0.3480 1.0000
4.750 0.8103 0.00883 0.00313 -0.0610 0.3200 1.0000
5.000 0.8369 0.00917 0.00338 -0.0608 0.2918 1.0000
5.250 0.8633 0.00954 0.00365 -0.0607 0.2626 1.0000
5.500 0.8894 0.00995 0.00397 -0.0605 0.2331 1.0000
5.750 0.9153 0.01038 0.00429 -0.0604 0.2048 1.0000
6.000 0.9409 0.01086 0.00465 -0.0601 0.1738 1.0000
6.250 0.9663 0.01137 0.00504 -0.0599 0.1450 1.0000
6.500 0.9914 0.01192 0.00548 -0.0597 0.1167 1.0000
6.750 1.0160 0.01254 0.00598 -0.0594 0.0888 1.0000
7.000 1.0401 0.01322 0.00654 -0.0590 0.0634 1.0000
7.250 1.0638 0.01397 0.00718 -0.0585 0.0421 1.0000
7.500 1.0865 0.01492 0.00803 -0.0579 0.0254 1.0000
7.750 1.1086 0.01595 0.00910 -0.0571 0.0173 1.0000
8.000 1.1321 0.01668 0.00991 -0.0565 0.0141 1.0000
8.250 1.1493 0.01845 0.01184 -0.0550 0.0114 1.0000
8.500 1.1714 0.01931 0.01283 -0.0542 0.0106 1.0000
8.750 1.1917 0.02039 0.01404 -0.0531 0.0098 1.0000
9.000 1.2123 0.02135 0.01508 -0.0523 0.0089 1.0000
9.250 1.2317 0.02240 0.01620 -0.0514 0.0081 1.0000
9.500 1.2442 0.02445 0.01840 -0.0496 0.0075 1.0000
9.750 1.2505 0.02763 0.02184 -0.0470 0.0072 1.0000
10.000 1.2672 0.02892 0.02330 -0.0457 0.0070 1.0000
10.250 1.2810 0.03057 0.02514 -0.0442 0.0069 1.0000
10.500 1.2920 0.03246 0.02724 -0.0424 0.0067 1.0000
10.750 1.2997 0.03461 0.02961 -0.0404 0.0065 1.0000
11.000 1.3020 0.03694 0.03220 -0.0378 0.0063 1.0000
11.250 1.2990 0.03948 0.03498 -0.0350 0.0062 1.0000
11.500 1.2927 0.04237 0.03810 -0.0327 0.0061 1.0000
11.750 1.2832 0.04580 0.04177 -0.0310 0.0061 1.0000
12.000 1.2713 0.04979 0.04600 -0.0304 0.0061 1.0000
12.250 1.2576 0.05442 0.05086 -0.0308 0.0061 1.0000
12.500 1.2420 0.05981 0.05648 -0.0325 0.0061 1.0000
12.750 1.2248 0.06602 0.06290 -0.0354 0.0061 1.0000
13.000 1.2066 0.07297 0.07005 -0.0392 0.0062 1.0000
13.250 1.1875 0.08067 0.07793 -0.0439 0.0062 1.0000
13.500 1.1676 0.08902 0.08645 -0.0491 0.0063 1.0000
13.750 1.1467 0.09803 0.09561 -0.0547 0.0064 1.0000
14.000 1.1256 0.10752 0.10522 -0.0605 0.0064 1.0000
14.250 1.1042 0.11768 0.11547 -0.0665 0.0065 1.0000
14.500 1.0811 0.12876 0.12665 -0.0729 0.0067 1.0000
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