D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.59 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1138-il-1000000.txt Download as CSV file: xf-dga1138-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1138
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4065 0.13834 0.13671 -0.0094 1.0000 0.0101
-13.250 -0.4038 0.13531 0.13368 -0.0104 1.0000 0.0108
-10.250 -0.7824 0.02526 0.02243 -0.0532 1.0000 0.0082
-10.000 -0.7676 0.02272 0.01956 -0.0520 1.0000 0.0085
-9.750 -0.7524 0.02023 0.01670 -0.0508 1.0000 0.0088
-9.500 -0.7378 0.01750 0.01355 -0.0492 1.0000 0.0096
-9.250 -0.7159 0.01683 0.01280 -0.0482 1.0000 0.0101
-9.000 -0.6940 0.01623 0.01211 -0.0471 1.0000 0.0106
-8.750 -0.6725 0.01554 0.01130 -0.0460 1.0000 0.0112
-8.500 -0.6516 0.01487 0.01050 -0.0447 1.0000 0.0117
-8.250 -0.6250 0.01414 0.00961 -0.0446 0.9994 0.0123
-8.000 -0.5932 0.01334 0.00871 -0.0456 0.9982 0.0138
-7.750 -0.5592 0.01337 0.00875 -0.0469 0.9969 0.0149
-7.500 -0.5251 0.01334 0.00869 -0.0483 0.9956 0.0161
-7.250 -0.4919 0.01278 0.00803 -0.0496 0.9945 0.0174
-7.000 -0.4588 0.01295 0.00824 -0.0507 0.9925 0.0186
-6.750 -0.4256 0.01320 0.00850 -0.0518 0.9902 0.0197
-6.500 -0.3923 0.01315 0.00840 -0.0529 0.9880 0.0211
-6.250 -0.3585 0.01318 0.00839 -0.0542 0.9861 0.0222
-6.000 -0.3261 0.01220 0.00728 -0.0554 0.9844 0.0240
-5.750 -0.2943 0.01202 0.00709 -0.0564 0.9808 0.0252
-5.500 -0.2634 0.01185 0.00688 -0.0570 0.9753 0.0264
-5.000 -0.1999 0.01135 0.00630 -0.0586 0.9606 0.0292
-4.750 -0.1689 0.01103 0.00590 -0.0592 0.9508 0.0301
-4.500 -0.1387 0.01111 0.00593 -0.0596 0.9399 0.0308
-4.250 -0.1121 0.00991 0.00460 -0.0593 0.9282 0.0319
-4.000 -0.0860 0.00917 0.00380 -0.0588 0.9170 0.0334
-3.750 -0.0591 0.00889 0.00349 -0.0585 0.9070 0.0347
-3.500 -0.0323 0.00865 0.00319 -0.0582 0.8970 0.0358
-3.250 -0.0053 0.00842 0.00290 -0.0579 0.8878 0.0366
-3.000 0.0220 0.00818 0.00262 -0.0577 0.8793 0.0373
-2.750 0.0492 0.00797 0.00237 -0.0575 0.8713 0.0379
-2.500 0.0767 0.00778 0.00214 -0.0573 0.8623 0.0385
-2.250 0.1043 0.00761 0.00194 -0.0571 0.8537 0.0394
-2.000 0.1318 0.00750 0.00179 -0.0569 0.8440 0.0406
-1.750 0.1595 0.00741 0.00167 -0.0568 0.8323 0.0416
-1.500 0.1866 0.00724 0.00143 -0.0566 0.8167 0.0440
-1.250 0.2137 0.00714 0.00126 -0.0563 0.7958 0.0470
-1.000 0.2405 0.00712 0.00113 -0.0559 0.7699 0.0500
-0.750 0.2673 0.00715 0.00104 -0.0556 0.7433 0.0534
-0.500 0.2937 0.00696 0.00100 -0.0554 0.7175 0.1337
-0.250 0.3202 0.00692 0.00102 -0.0552 0.6864 0.1856
0.000 0.3445 0.00719 0.00105 -0.0545 0.5833 0.2267
0.250 0.3698 0.00736 0.00116 -0.0542 0.5333 0.2849
0.500 0.3871 0.00589 0.00125 -0.0526 0.5170 0.8372
0.750 0.4501 0.00589 0.00146 -0.0605 0.4969 0.9993
1.000 0.4792 0.00601 0.00151 -0.0609 0.4812 1.0000
1.250 0.5054 0.00612 0.00156 -0.0605 0.4647 1.0000
1.500 0.5314 0.00624 0.00161 -0.0602 0.4441 1.0000
1.750 0.5568 0.00643 0.00166 -0.0598 0.4036 1.0000
2.000 0.5779 0.00721 0.00188 -0.0587 0.2758 1.0000
2.250 0.6001 0.00787 0.00213 -0.0579 0.1867 1.0000
2.500 0.6255 0.00809 0.00228 -0.0575 0.1715 1.0000
2.750 0.6510 0.00827 0.00241 -0.0571 0.1621 1.0000
3.000 0.6769 0.00842 0.00255 -0.0568 0.1540 1.0000
3.250 0.7024 0.00861 0.00268 -0.0564 0.1416 1.0000
3.500 0.7279 0.00880 0.00283 -0.0560 0.1252 1.0000
3.750 0.7515 0.00927 0.00305 -0.0554 0.0815 1.0000
4.000 0.7732 0.01003 0.00349 -0.0544 0.0237 1.0000
4.250 0.7979 0.01039 0.00385 -0.0538 0.0168 1.0000
4.500 0.8230 0.01069 0.00420 -0.0534 0.0154 1.0000
4.750 0.8477 0.01105 0.00460 -0.0529 0.0140 1.0000
5.000 0.8718 0.01152 0.00512 -0.0522 0.0128 1.0000
5.250 0.8941 0.01229 0.00601 -0.0512 0.0116 1.0000
5.500 0.9192 0.01258 0.00632 -0.0508 0.0110 1.0000
5.750 0.9432 0.01304 0.00683 -0.0502 0.0104 1.0000
6.000 0.9666 0.01359 0.00743 -0.0495 0.0098 1.0000
6.250 0.9896 0.01418 0.00807 -0.0487 0.0094 1.0000
6.500 1.0121 0.01482 0.00875 -0.0480 0.0089 1.0000
6.750 1.0334 0.01562 0.00960 -0.0470 0.0085 1.0000
7.000 1.0486 0.01737 0.01147 -0.0450 0.0080 1.0000
7.250 1.0680 0.01862 0.01281 -0.0437 0.0077 1.0000
7.500 1.0902 0.01932 0.01360 -0.0429 0.0075 1.0000
7.750 1.1115 0.02019 0.01456 -0.0419 0.0072 1.0000
8.000 1.1322 0.02111 0.01558 -0.0409 0.0069 1.0000
8.250 1.1518 0.02224 0.01682 -0.0398 0.0066 1.0000
8.500 1.1699 0.02367 0.01840 -0.0384 0.0065 1.0000
8.750 1.1869 0.02526 0.02016 -0.0369 0.0064 1.0000
9.000 1.2026 0.02695 0.02202 -0.0353 0.0063 1.0000
9.250 1.2163 0.02886 0.02413 -0.0335 0.0062 1.0000
9.500 1.2285 0.03069 0.02614 -0.0315 0.0061 1.0000
9.750 1.2389 0.03254 0.02817 -0.0294 0.0060 1.0000
10.000 1.2475 0.03435 0.03014 -0.0272 0.0059 1.0000
10.250 1.2558 0.03586 0.03177 -0.0251 0.0058 1.0000
10.500 1.2586 0.03771 0.03379 -0.0223 0.0057 1.0000
10.750 1.2551 0.03955 0.03577 -0.0186 0.0056 1.0000
11.000 1.2489 0.04161 0.03796 -0.0150 0.0055 1.0000
11.250 1.2378 0.04439 0.04093 -0.0118 0.0055 1.0000
11.500 1.2251 0.04758 0.04430 -0.0095 0.0054 1.0000
11.750 1.2092 0.05147 0.04838 -0.0080 0.0054 1.0000
12.000 1.1922 0.05595 0.05305 -0.0078 0.0054 1.0000
12.250 1.1740 0.06120 0.05847 -0.0089 0.0054 1.0000
12.500 1.1558 0.06719 0.06464 -0.0114 0.0054 1.0000
12.750 1.1371 0.07440 0.07203 -0.0158 0.0054 1.0000
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Polar data table (+)
Polar graphs
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