D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 500,000 Max Cl/Cd: 79.82 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1138-il-500000.txt Download as CSV file: xf-dga1138-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3948 0.08469 0.08253 -0.0268 1.0000 0.0226
-9.500 -0.3975 0.08020 0.07806 -0.0281 1.0000 0.0227
-9.250 -0.4014 0.07571 0.07359 -0.0294 1.0000 0.0227
-9.000 -0.4076 0.07122 0.06912 -0.0307 1.0000 0.0227
-8.750 -0.4178 0.06707 0.06501 -0.0316 1.0000 0.0227
-8.500 -0.4292 0.06285 0.06082 -0.0328 1.0000 0.0227
-8.250 -0.4352 0.05781 0.05578 -0.0348 1.0000 0.0227
-7.500 -0.4822 0.05324 0.05085 -0.0396 1.0000 0.0218
-7.250 -0.4789 0.04650 0.04395 -0.0406 1.0000 0.0214
-7.000 -0.4669 0.04895 0.04648 -0.0379 1.0000 0.0256
-6.750 -0.4520 0.04418 0.04155 -0.0391 0.9992 0.0270
-6.500 -0.4324 0.02178 0.01700 -0.0443 0.9957 0.0235
-6.250 -0.3992 0.02138 0.01664 -0.0462 0.9941 0.0251
-6.000 -0.3670 0.02085 0.01604 -0.0474 0.9914 0.0275
-5.750 -0.3341 0.01960 0.01445 -0.0484 0.9887 0.0297
-5.500 -0.3022 0.01754 0.01197 -0.0496 0.9865 0.0322
-5.250 -0.2693 0.01650 0.01094 -0.0513 0.9848 0.0350
-5.000 -0.2351 0.01556 0.00985 -0.0527 0.9830 0.0371
-4.750 -0.2037 0.01474 0.00887 -0.0534 0.9785 0.0389
-4.500 -0.1692 0.01431 0.00831 -0.0547 0.9755 0.0407
-4.250 -0.1331 0.01380 0.00768 -0.0563 0.9730 0.0415
-4.000 -0.0977 0.01253 0.00627 -0.0579 0.9707 0.0426
-3.750 -0.0690 0.01135 0.00508 -0.0581 0.9640 0.0445
-3.500 -0.0364 0.01069 0.00442 -0.0591 0.9596 0.0457
-3.250 -0.0052 0.01019 0.00390 -0.0597 0.9528 0.0467
-3.000 0.0266 0.00975 0.00343 -0.0604 0.9451 0.0476
-2.750 0.0561 0.00940 0.00305 -0.0606 0.9360 0.0486
-2.500 0.0857 0.00910 0.00273 -0.0608 0.9283 0.0502
-2.250 0.1137 0.00887 0.00246 -0.0607 0.9188 0.0520
-2.000 0.1413 0.00869 0.00223 -0.0604 0.9097 0.0534
-1.750 0.1689 0.00854 0.00201 -0.0602 0.9010 0.0558
-1.500 0.1959 0.00840 0.00185 -0.0598 0.8914 0.0604
-1.250 0.2228 0.00825 0.00172 -0.0595 0.8812 0.0722
-1.000 0.2490 0.00796 0.00171 -0.0591 0.8706 0.1620
-0.750 0.2757 0.00780 0.00172 -0.0588 0.8597 0.2148
-0.500 0.3021 0.00763 0.00171 -0.0585 0.8465 0.2702
-0.250 0.3264 0.00708 0.00167 -0.0579 0.8288 0.4537
0.000 0.3844 0.00580 0.00178 -0.0645 0.8033 1.0000
0.250 0.4096 0.00588 0.00172 -0.0637 0.7756 1.0000
0.500 0.4350 0.00598 0.00170 -0.0631 0.7490 1.0000
0.750 0.4603 0.00610 0.00169 -0.0624 0.7220 1.0000
1.000 0.4852 0.00627 0.00170 -0.0617 0.6853 1.0000
1.250 0.5084 0.00657 0.00171 -0.0606 0.6076 1.0000
1.500 0.5308 0.00702 0.00182 -0.0596 0.5464 1.0000
1.750 0.5557 0.00728 0.00196 -0.0590 0.5229 1.0000
2.000 0.5809 0.00750 0.00209 -0.0585 0.5038 1.0000
2.250 0.6063 0.00770 0.00223 -0.0580 0.4847 1.0000
2.500 0.6314 0.00791 0.00237 -0.0575 0.4509 1.0000
2.750 0.6528 0.00856 0.00251 -0.0565 0.3326 1.0000
3.000 0.6729 0.00948 0.00288 -0.0554 0.2190 1.0000
3.250 0.6969 0.00991 0.00314 -0.0549 0.1889 1.0000
3.500 0.7215 0.01024 0.00341 -0.0544 0.1718 1.0000
3.750 0.7465 0.01054 0.00366 -0.0540 0.1573 1.0000
4.000 0.7718 0.01079 0.00388 -0.0536 0.1402 1.0000
4.250 0.7957 0.01125 0.00408 -0.0531 0.0922 1.0000
4.500 0.8165 0.01217 0.00465 -0.0521 0.0311 1.0000
4.750 0.8402 0.01271 0.00519 -0.0513 0.0224 1.0000
5.000 0.8641 0.01322 0.00577 -0.0506 0.0199 1.0000
5.250 0.8872 0.01388 0.00651 -0.0497 0.0181 1.0000
5.500 0.9083 0.01481 0.00757 -0.0485 0.0169 1.0000
5.750 0.9309 0.01547 0.00833 -0.0476 0.0164 1.0000
6.000 0.9532 0.01618 0.00910 -0.0466 0.0155 1.0000
6.250 0.9747 0.01697 0.00995 -0.0456 0.0145 1.0000
6.500 0.9953 0.01793 0.01098 -0.0444 0.0140 1.0000
6.750 1.0156 0.01898 0.01211 -0.0432 0.0135 1.0000
7.000 1.0353 0.02018 0.01338 -0.0420 0.0131 1.0000
7.250 1.0547 0.02160 0.01491 -0.0407 0.0127 1.0000
7.500 1.0740 0.02334 0.01675 -0.0394 0.0125 1.0000
7.750 1.0940 0.02508 0.01865 -0.0381 0.0125 1.0000
8.000 1.1134 0.02765 0.02164 -0.0362 0.0138 1.0000
8.250 1.1280 0.03088 0.02529 -0.0340 0.0147 1.0000
8.500 1.1381 0.03449 0.02929 -0.0315 0.0156 1.0000
8.750 1.1441 0.03999 0.03549 -0.0273 0.0209 1.0000
9.000 1.1508 0.04236 0.03809 -0.0249 0.0200 1.0000
9.250 1.1555 0.04478 0.04071 -0.0226 0.0193 1.0000
9.500 1.1612 0.04722 0.04323 -0.0207 0.0186 1.0000
9.750 1.1618 0.05037 0.04648 -0.0185 0.0181 1.0000
10.000 1.1483 0.05494 0.05125 -0.0153 0.0176 1.0000
10.250 1.1205 0.05965 0.05618 -0.0107 0.0174 1.0000
10.500 1.0920 0.06425 0.06099 -0.0076 0.0172 1.0000
10.750 1.0672 0.06886 0.06579 -0.0065 0.0172 1.0000
11.000 1.0453 0.07373 0.07083 -0.0071 0.0172 1.0000
11.250 1.0295 0.07843 0.07566 -0.0090 0.0172 1.0000
11.500 1.0161 0.08354 0.08090 -0.0121 0.0173 1.0000
11.750 1.0045 0.08934 0.08682 -0.0166 0.0174 1.0000
12.000 0.9919 0.09680 0.09444 -0.0233 0.0177 1.0000
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Polar data table (+)
Polar graphs
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