AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Reynolds number: 200,000 Max Cl/Cd: 66.61 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag25-il-200000-n5.txt Download as CSV file: xf-ag25-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: AG25 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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4853 0.08715 0.08377 -0.0093 1.0000 0.0174
-7.750 -0.4831 0.08296 0.07963 -0.0118 1.0000 0.0168
-7.500 -0.4806 0.07826 0.07498 -0.0155 1.0000 0.0158
-7.250 -0.4746 0.07180 0.06855 -0.0225 1.0000 0.0146
-6.750 -0.4467 0.05103 0.04756 -0.0447 1.0000 0.0121
-6.500 -0.4336 0.04367 0.03993 -0.0501 1.0000 0.0118
-6.250 -0.4181 0.03722 0.03307 -0.0536 1.0000 0.0116
-6.000 -0.3998 0.03183 0.02718 -0.0555 1.0000 0.0115
-5.750 -0.3789 0.02749 0.02228 -0.0564 1.0000 0.0114
-5.500 -0.3561 0.02411 0.01836 -0.0567 1.0000 0.0115
-5.250 -0.3322 0.02154 0.01530 -0.0565 1.0000 0.0117
-5.000 -0.3078 0.01960 0.01294 -0.0562 1.0000 0.0121
-4.750 -0.2832 0.01781 0.01085 -0.0558 1.0000 0.0126
-4.500 -0.2584 0.01621 0.00908 -0.0555 1.0000 0.0136
-4.250 -0.2295 0.01560 0.00840 -0.0561 0.9982 0.0161
-4.000 -0.1927 0.01463 0.00727 -0.0580 0.9942 0.0184
-3.750 -0.1570 0.01347 0.00598 -0.0597 0.9890 0.0206
-3.500 -0.1197 0.01272 0.00513 -0.0619 0.9841 0.0260
-3.250 -0.0835 0.01207 0.00442 -0.0637 0.9780 0.0361
-3.000 -0.0476 0.01145 0.00387 -0.0654 0.9711 0.0625
-2.750 -0.0134 0.01086 0.00350 -0.0670 0.9627 0.1217
-2.500 0.0217 0.01030 0.00323 -0.0688 0.9548 0.2076
-2.250 0.0537 0.00985 0.00305 -0.0698 0.9436 0.2941
-2.000 0.0852 0.00951 0.00291 -0.0706 0.9318 0.3695
-1.750 0.1157 0.00921 0.00279 -0.0710 0.9190 0.4403
-1.500 0.1449 0.00893 0.00267 -0.0711 0.9050 0.5072
-1.250 0.1728 0.00868 0.00258 -0.0708 0.8898 0.5732
-1.000 0.1992 0.00843 0.00251 -0.0700 0.8737 0.6438
-0.750 0.2235 0.00817 0.00246 -0.0687 0.8565 0.7227
-0.500 0.2450 0.00793 0.00238 -0.0666 0.8382 0.8137
-0.250 0.2720 0.00767 0.00223 -0.0654 0.8195 0.9466
0.000 0.3019 0.00770 0.00212 -0.0656 0.7993 1.0000
0.250 0.3291 0.00778 0.00206 -0.0652 0.7782 1.0000
0.500 0.3562 0.00789 0.00202 -0.0648 0.7563 1.0000
1.000 0.4104 0.00814 0.00199 -0.0641 0.7098 1.0000
1.250 0.4374 0.00829 0.00201 -0.0637 0.6852 1.0000
1.500 0.4643 0.00845 0.00205 -0.0633 0.6596 1.0000
1.750 0.4912 0.00864 0.00210 -0.0630 0.6331 1.0000
2.000 0.5181 0.00884 0.00217 -0.0627 0.6058 1.0000
2.250 0.5449 0.00905 0.00225 -0.0623 0.5779 1.0000
2.500 0.5716 0.00929 0.00239 -0.0620 0.5495 1.0000
2.750 0.5982 0.00954 0.00252 -0.0618 0.5209 1.0000
3.000 0.6248 0.00980 0.00268 -0.0615 0.4922 1.0000
3.250 0.6514 0.01008 0.00285 -0.0612 0.4635 1.0000
3.750 0.7042 0.01070 0.00330 -0.0607 0.4067 1.0000
4.000 0.7305 0.01103 0.00355 -0.0604 0.3784 1.0000
4.250 0.7567 0.01138 0.00382 -0.0602 0.3502 1.0000
4.500 0.7827 0.01175 0.00412 -0.0600 0.3225 1.0000
4.750 0.8087 0.01215 0.00447 -0.0597 0.2947 1.0000
5.000 0.8345 0.01257 0.00482 -0.0595 0.2671 1.0000
5.250 0.8601 0.01301 0.00520 -0.0592 0.2402 1.0000
5.500 0.8855 0.01348 0.00562 -0.0589 0.2135 1.0000
5.750 0.9108 0.01399 0.00607 -0.0586 0.1875 1.0000
6.000 0.9358 0.01453 0.00659 -0.0583 0.1624 1.0000
6.250 0.9604 0.01512 0.00712 -0.0580 0.1378 1.0000
6.500 0.9848 0.01576 0.00771 -0.0576 0.1146 1.0000
6.750 1.0088 0.01645 0.00835 -0.0572 0.0912 1.0000
7.000 1.0324 0.01719 0.00905 -0.0568 0.0708 1.0000
7.250 1.0553 0.01804 0.00984 -0.0563 0.0532 1.0000
7.500 1.0780 0.01893 0.01077 -0.0557 0.0389 1.0000
7.750 1.0999 0.01993 0.01178 -0.0550 0.0284 1.0000
8.000 1.1209 0.02106 0.01296 -0.0542 0.0210 1.0000
8.250 1.1419 0.02215 0.01423 -0.0533 0.0173 1.0000
8.500 1.1614 0.02340 0.01556 -0.0524 0.0139 1.0000
8.750 1.1799 0.02475 0.01708 -0.0513 0.0119 1.0000
9.000 1.1976 0.02616 0.01869 -0.0501 0.0107 1.0000
9.250 1.2142 0.02766 0.02035 -0.0488 0.0098 1.0000
9.500 1.2292 0.02929 0.02220 -0.0475 0.0091 1.0000
9.750 1.2407 0.03132 0.02440 -0.0459 0.0085 1.0000
10.000 1.2469 0.03414 0.02745 -0.0438 0.0081 1.0000
10.250 1.2563 0.03633 0.02988 -0.0420 0.0078 1.0000
10.500 1.2651 0.03834 0.03217 -0.0403 0.0074 1.0000
10.750 1.2699 0.04039 0.03447 -0.0383 0.0070 1.0000
11.000 1.2709 0.04257 0.03689 -0.0362 0.0065 1.0000
11.250 1.2693 0.04501 0.03956 -0.0345 0.0062 1.0000
11.500 1.2651 0.04788 0.04265 -0.0334 0.0060 1.0000
11.750 1.2584 0.05133 0.04633 -0.0330 0.0058 1.0000
12.000 1.2490 0.05550 0.05074 -0.0336 0.0058 1.0000
12.250 1.2378 0.06035 0.05582 -0.0352 0.0057 1.0000
12.500 1.2245 0.06602 0.06172 -0.0378 0.0057 1.0000
12.750 1.2095 0.07253 0.06845 -0.0414 0.0057 1.0000
13.000 1.1921 0.08001 0.07615 -0.0459 0.0057 1.0000
13.250 1.1730 0.08836 0.08470 -0.0511 0.0057 1.0000
13.500 1.1507 0.09786 0.09439 -0.0569 0.0058 1.0000
13.750 1.1272 0.10807 0.10476 -0.0630 0.0060 1.0000
14.000 1.1000 0.11973 0.11656 -0.0697 0.0063 1.0000
14.250 1.0671 0.13383 0.13077 -0.0774 0.0069 1.0000
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Polar data table (+)
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