AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Reynolds number: 500,000 Max Cl/Cd: 91.28 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ag27-il-500000.txt Download as CSV file: xf-ag27-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3974 0.09674 0.09463 -0.0009 1.0000 0.0124
-8.750 -0.3943 0.09312 0.09102 -0.0017 1.0000 0.0128
-8.500 -0.5076 0.10058 0.09838 0.0064 1.0000 0.0114
-8.250 -0.5009 0.09754 0.09535 0.0059 1.0000 0.0118
-8.000 -0.4944 0.09441 0.09224 0.0047 1.0000 0.0121
-7.750 -0.4882 0.09119 0.08904 0.0031 1.0000 0.0125
-7.500 -0.4824 0.08781 0.08569 0.0011 1.0000 0.0129
-7.250 -0.4757 0.08426 0.08216 -0.0016 1.0000 0.0134
-7.000 -0.4646 0.08011 0.07801 -0.0061 1.0000 0.0142
-6.750 -0.4500 0.07541 0.07331 -0.0120 1.0000 0.0152
-6.500 -0.4244 0.06997 0.06786 -0.0213 1.0000 0.0165
-6.250 -0.4000 0.06475 0.06261 -0.0287 1.0000 0.0168
-6.000 -0.3743 0.05876 0.05656 -0.0363 1.0000 0.0169
-5.750 -0.3577 0.04824 0.04591 -0.0459 1.0000 0.0179
-5.500 -0.3394 0.04575 0.04338 -0.0474 1.0000 0.0187
-5.250 -0.3169 0.04190 0.03942 -0.0501 1.0000 0.0195
-5.000 -0.2928 0.03759 0.03495 -0.0528 1.0000 0.0205
-4.750 -0.2675 0.03317 0.03029 -0.0550 1.0000 0.0219
-4.500 -0.2403 0.02968 0.02648 -0.0557 1.0000 0.0245
-4.250 -0.2146 0.02856 0.02503 -0.0552 1.0000 0.0255
-4.000 -0.1863 0.01862 0.01424 -0.0572 1.0000 0.0160
-3.750 -0.1573 0.01423 0.00918 -0.0575 1.0000 0.0137
-3.500 -0.1299 0.01241 0.00706 -0.0572 0.9999 0.0138
-3.250 -0.0919 0.01119 0.00564 -0.0591 0.9973 0.0152
-3.000 -0.0532 0.01053 0.00486 -0.0612 0.9943 0.0167
-2.750 -0.0163 0.00928 0.00352 -0.0631 0.9902 0.0202
-2.500 0.0224 0.00874 0.00291 -0.0652 0.9858 0.0250
-2.250 0.0611 0.00803 0.00221 -0.0673 0.9812 0.0459
-2.000 0.0960 0.00751 0.00189 -0.0688 0.9724 0.1037
-1.750 0.1293 0.00705 0.00173 -0.0700 0.9616 0.1933
-1.500 0.1603 0.00667 0.00163 -0.0707 0.9482 0.2876
-1.250 0.1885 0.00636 0.00154 -0.0706 0.9318 0.3749
-1.000 0.2148 0.00609 0.00148 -0.0700 0.9138 0.4656
-0.750 0.2399 0.00575 0.00144 -0.0692 0.8936 0.5807
-0.500 0.2612 0.00472 0.00137 -0.0669 0.8735 1.0000
-0.250 0.2876 0.00479 0.00130 -0.0663 0.8515 1.0000
0.000 0.3140 0.00489 0.00124 -0.0657 0.8288 1.0000
0.250 0.3407 0.00499 0.00120 -0.0651 0.8041 1.0000
0.500 0.3676 0.00510 0.00117 -0.0646 0.7784 1.0000
0.750 0.3945 0.00524 0.00115 -0.0642 0.7517 1.0000
1.000 0.4215 0.00538 0.00115 -0.0638 0.7243 1.0000
1.250 0.4485 0.00554 0.00117 -0.0634 0.6961 1.0000
1.500 0.4756 0.00570 0.00121 -0.0631 0.6669 1.0000
1.750 0.5027 0.00588 0.00125 -0.0628 0.6377 1.0000
2.000 0.5297 0.00608 0.00130 -0.0625 0.6076 1.0000
2.250 0.5568 0.00628 0.00137 -0.0623 0.5764 1.0000
2.500 0.5839 0.00649 0.00146 -0.0620 0.5431 1.0000
2.750 0.6108 0.00674 0.00158 -0.0618 0.5087 1.0000
3.000 0.6377 0.00700 0.00170 -0.0616 0.4717 1.0000
3.250 0.6645 0.00728 0.00184 -0.0613 0.4361 1.0000
3.500 0.6911 0.00760 0.00200 -0.0611 0.3970 1.0000
3.750 0.7178 0.00792 0.00220 -0.0610 0.3591 1.0000
4.000 0.7443 0.00828 0.00240 -0.0608 0.3209 1.0000
4.250 0.7707 0.00867 0.00263 -0.0606 0.2815 1.0000
4.500 0.7970 0.00906 0.00289 -0.0604 0.2470 1.0000
4.750 0.8232 0.00947 0.00319 -0.0602 0.2133 1.0000
5.000 0.8493 0.00989 0.00349 -0.0600 0.1829 1.0000
5.250 0.8755 0.01031 0.00382 -0.0598 0.1589 1.0000
5.500 0.9014 0.01076 0.00417 -0.0595 0.1369 1.0000
5.750 0.9275 0.01115 0.00453 -0.0593 0.1197 1.0000
6.000 0.9535 0.01157 0.00493 -0.0590 0.1038 1.0000
6.250 0.9793 0.01200 0.00534 -0.0587 0.0905 1.0000
6.500 1.0050 0.01245 0.00577 -0.0585 0.0783 1.0000
6.750 1.0305 0.01291 0.00622 -0.0581 0.0669 1.0000
7.000 1.0558 0.01340 0.00671 -0.0578 0.0564 1.0000
7.250 1.0807 0.01396 0.00728 -0.0574 0.0463 1.0000
7.500 1.1051 0.01462 0.00792 -0.0570 0.0363 1.0000
7.750 1.1292 0.01531 0.00861 -0.0565 0.0274 1.0000
8.000 1.1536 0.01593 0.00927 -0.0561 0.0211 1.0000
8.250 1.1759 0.01700 0.01044 -0.0553 0.0161 1.0000
8.500 1.1974 0.01817 0.01169 -0.0544 0.0127 1.0000
8.750 1.2179 0.01948 0.01317 -0.0534 0.0108 1.0000
9.000 1.2406 0.02026 0.01406 -0.0528 0.0093 1.0000
9.250 1.2607 0.02147 0.01538 -0.0519 0.0083 1.0000
9.500 1.2712 0.02443 0.01863 -0.0499 0.0074 1.0000
9.750 1.2891 0.02593 0.02032 -0.0487 0.0071 1.0000
10.000 1.3057 0.02757 0.02218 -0.0474 0.0067 1.0000
10.250 1.3195 0.02956 0.02440 -0.0459 0.0063 1.0000
10.500 1.3306 0.03182 0.02692 -0.0442 0.0061 1.0000
10.750 1.3382 0.03437 0.02974 -0.0423 0.0059 1.0000
11.000 1.3413 0.03722 0.03287 -0.0403 0.0057 1.0000
11.250 1.3383 0.04027 0.03622 -0.0378 0.0057 1.0000
11.500 1.3275 0.04345 0.03965 -0.0351 0.0057 1.0000
11.750 1.3137 0.04724 0.04370 -0.0337 0.0057 1.0000
12.000 1.2974 0.05202 0.04872 -0.0341 0.0057 1.0000
12.250 1.2803 0.05780 0.05474 -0.0366 0.0057 1.0000
12.500 1.2619 0.06481 0.06197 -0.0408 0.0058 1.0000
12.750 1.2425 0.07293 0.07029 -0.0464 0.0058 1.0000
13.000 1.2216 0.08212 0.07967 -0.0528 0.0059 1.0000
13.250 1.2003 0.09194 0.08964 -0.0593 0.0059 1.0000
13.500 1.1773 0.10236 0.10018 -0.0656 0.0060 1.0000
13.750 1.1527 0.11338 0.11130 -0.0718 0.0062 1.0000
14.000 1.1268 0.12492 0.12293 -0.0779 0.0063 1.0000
14.250 1.0979 0.13777 0.13584 -0.0844 0.0066 1.0000
14.500 0.9391 0.12457 0.12258 -0.0572 0.0069 1.0000
14.750 0.9026 0.13190 0.12997 -0.0601 0.0072 1.0000
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Polar data table (+)
Polar graphs
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