AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: AG24 Bubble Dancer DLG by Mark Drela (ag24-il) Reynolds number: 200,000 Max Cl/Cd: 66.48 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ag24-il-200000-n5.txt Download as CSV file: xf-ag24-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5141 0.10427 0.10074 -0.0027 1.0000 0.0157
-9.250 -0.5115 0.10023 0.09672 -0.0043 1.0000 0.0151
-9.000 -0.5096 0.09591 0.09243 -0.0064 1.0000 0.0146
-8.750 -0.5086 0.09135 0.08791 -0.0088 1.0000 0.0141
-8.500 -0.5084 0.08651 0.08311 -0.0116 1.0000 0.0137
-8.250 -0.5096 0.08129 0.07793 -0.0150 1.0000 0.0133
-8.000 -0.5130 0.07539 0.07210 -0.0195 1.0000 0.0128
-7.750 -0.5146 0.06612 0.06287 -0.0300 1.0000 0.0122
-7.250 -0.5092 0.04079 0.03671 -0.0518 1.0000 0.0109
-7.000 -0.4979 0.03550 0.03096 -0.0537 1.0000 0.0109
-6.750 -0.4828 0.03121 0.02615 -0.0545 1.0000 0.0109
-6.500 -0.4651 0.02761 0.02206 -0.0546 1.0000 0.0110
-6.250 -0.4459 0.02420 0.01811 -0.0546 1.0000 0.0113
-6.000 -0.4246 0.02197 0.01558 -0.0542 1.0000 0.0117
-5.750 -0.4023 0.02042 0.01380 -0.0537 1.0000 0.0123
-5.500 -0.3793 0.01910 0.01228 -0.0532 1.0000 0.0130
-5.250 -0.3562 0.01818 0.01119 -0.0526 1.0000 0.0144
-5.000 -0.3309 0.01737 0.01021 -0.0522 0.9994 0.0162
-4.750 -0.2957 0.01582 0.00848 -0.0540 0.9957 0.0175
-4.500 -0.2604 0.01467 0.00722 -0.0559 0.9914 0.0196
-4.250 -0.2244 0.01392 0.00637 -0.0578 0.9865 0.0230
-4.000 -0.1868 0.01316 0.00553 -0.0600 0.9824 0.0293
-3.750 -0.1521 0.01254 0.00483 -0.0615 0.9757 0.0384
-3.500 -0.1159 0.01191 0.00426 -0.0634 0.9700 0.0639
-3.250 -0.0829 0.01130 0.00387 -0.0648 0.9618 0.1182
-3.000 -0.0480 0.01074 0.00358 -0.0666 0.9549 0.1933
-2.750 -0.0168 0.01030 0.00338 -0.0675 0.9445 0.2683
-2.500 0.0145 0.00994 0.00320 -0.0682 0.9341 0.3361
-2.250 0.0452 0.00963 0.00305 -0.0688 0.9232 0.3975
-2.000 0.0749 0.00937 0.00293 -0.0690 0.9114 0.4554
-1.750 0.1034 0.00913 0.00282 -0.0689 0.8985 0.5095
-1.500 0.1308 0.00893 0.00272 -0.0685 0.8847 0.5622
-1.250 0.1574 0.00873 0.00264 -0.0679 0.8699 0.6143
-1.000 0.1832 0.00856 0.00259 -0.0670 0.8543 0.6666
-0.750 0.2081 0.00841 0.00254 -0.0659 0.8380 0.7198
-0.250 0.2549 0.00818 0.00244 -0.0628 0.8038 0.8272
0.000 0.2780 0.00808 0.00236 -0.0611 0.7857 0.8843
0.750 0.3665 0.00814 0.00214 -0.0613 0.7245 1.0000
1.000 0.3939 0.00827 0.00213 -0.0611 0.7027 1.0000
1.250 0.4212 0.00841 0.00215 -0.0608 0.6796 1.0000
1.500 0.4485 0.00856 0.00218 -0.0606 0.6561 1.0000
1.750 0.4756 0.00873 0.00223 -0.0603 0.6320 1.0000
2.000 0.5027 0.00892 0.00229 -0.0601 0.6072 1.0000
2.250 0.5298 0.00912 0.00240 -0.0599 0.5818 1.0000
2.500 0.5568 0.00934 0.00251 -0.0597 0.5565 1.0000
2.750 0.5837 0.00957 0.00263 -0.0594 0.5311 1.0000
3.000 0.6105 0.00982 0.00278 -0.0592 0.5056 1.0000
3.250 0.6373 0.01008 0.00294 -0.0590 0.4801 1.0000
3.500 0.6640 0.01035 0.00316 -0.0588 0.4547 1.0000
3.750 0.6906 0.01063 0.00337 -0.0586 0.4292 1.0000
4.000 0.7171 0.01094 0.00360 -0.0584 0.4034 1.0000
4.250 0.7435 0.01126 0.00386 -0.0582 0.3777 1.0000
4.500 0.7697 0.01161 0.00416 -0.0580 0.3519 1.0000
4.750 0.7958 0.01197 0.00447 -0.0577 0.3254 1.0000
5.000 0.8216 0.01237 0.00480 -0.0575 0.2982 1.0000
5.250 0.8473 0.01279 0.00516 -0.0573 0.2710 1.0000
5.500 0.8728 0.01325 0.00558 -0.0570 0.2433 1.0000
5.750 0.8980 0.01375 0.00601 -0.0567 0.2155 1.0000
6.000 0.9229 0.01428 0.00648 -0.0564 0.1882 1.0000
6.250 0.9475 0.01486 0.00699 -0.0561 0.1609 1.0000
6.500 0.9718 0.01549 0.00754 -0.0557 0.1340 1.0000
6.750 0.9956 0.01619 0.00819 -0.0554 0.1076 1.0000
7.000 1.0188 0.01697 0.00888 -0.0549 0.0819 1.0000
7.250 1.0415 0.01782 0.00965 -0.0544 0.0602 1.0000
7.500 1.0639 0.01870 0.01050 -0.0538 0.0433 1.0000
7.750 1.0857 0.01966 0.01147 -0.0531 0.0314 1.0000
8.000 1.1068 0.02071 0.01256 -0.0524 0.0234 1.0000
8.250 1.1268 0.02189 0.01380 -0.0514 0.0185 1.0000
8.750 1.1658 0.02420 0.01645 -0.0495 0.0136 1.0000
9.000 1.1814 0.02577 0.01812 -0.0482 0.0115 1.0000
9.250 1.1983 0.02713 0.01966 -0.0470 0.0107 1.0000
9.500 1.2133 0.02867 0.02139 -0.0455 0.0099 1.0000
9.750 1.2268 0.03032 0.02323 -0.0440 0.0093 1.0000
10.000 1.2389 0.03206 0.02515 -0.0424 0.0088 1.0000
10.250 1.2493 0.03389 0.02714 -0.0407 0.0084 1.0000
10.500 1.2574 0.03583 0.02926 -0.0389 0.0081 1.0000
10.750 1.2610 0.03790 0.03151 -0.0366 0.0078 1.0000
11.000 1.2613 0.04029 0.03409 -0.0344 0.0076 1.0000
11.250 1.2588 0.04306 0.03706 -0.0325 0.0075 1.0000
11.500 1.2532 0.04632 0.04059 -0.0310 0.0073 1.0000
12.000 1.2366 0.05397 0.04873 -0.0301 0.0071 1.0000
12.250 1.2287 0.05806 0.05307 -0.0308 0.0070 1.0000
12.500 1.2190 0.06275 0.05801 -0.0325 0.0069 1.0000
12.750 1.2071 0.06818 0.06367 -0.0349 0.0068 1.0000
13.000 1.1930 0.07435 0.07006 -0.0381 0.0068 1.0000
13.250 1.1774 0.08122 0.07714 -0.0420 0.0068 1.0000
13.500 1.1607 0.08869 0.08480 -0.0465 0.0068 1.0000
13.750 1.1419 0.09690 0.09317 -0.0513 0.0069 1.0000
14.000 1.1231 0.10547 0.10189 -0.0564 0.0070 1.0000
14.250 1.1038 0.11460 0.11115 -0.0617 0.0071 1.0000
14.500 0.9194 0.11451 0.11125 -0.0438 0.0081 1.0000
14.750 0.8817 0.12285 0.11975 -0.0477 0.0084 1.0000
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Polar data table (+)
Polar graphs
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