D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 100,000 Max Cl/Cd: 49.2 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1138-il-100000-n5.txt Download as CSV file: xf-dga1138-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4887 0.09069 0.08578 -0.0200 1.0000 0.0310
-8.750 -0.4915 0.08684 0.08200 -0.0219 1.0000 0.0312
-8.500 -0.4914 0.08249 0.07770 -0.0248 1.0000 0.0312
-8.250 -0.4895 0.07782 0.07305 -0.0280 1.0000 0.0310
-8.000 -0.4862 0.07290 0.06813 -0.0312 1.0000 0.0308
-7.750 -0.4814 0.06773 0.06292 -0.0342 1.0000 0.0308
-7.500 -0.4748 0.06225 0.05737 -0.0371 1.0000 0.0309
-7.250 -0.4660 0.05641 0.05138 -0.0396 1.0000 0.0315
-7.000 -0.4554 0.04901 0.04367 -0.0423 1.0000 0.0331
-6.750 -0.4446 0.04072 0.03457 -0.0440 1.0000 0.0348
-6.500 -0.4320 0.03616 0.02952 -0.0436 1.0000 0.0362
-6.250 -0.4157 0.03432 0.02764 -0.0425 1.0000 0.0384
-6.000 -0.3982 0.03196 0.02486 -0.0416 1.0000 0.0425
-5.750 -0.3791 0.02915 0.02130 -0.0404 1.0000 0.0450
-5.500 -0.3602 0.02671 0.01845 -0.0394 1.0000 0.0481
-5.250 -0.3401 0.02531 0.01690 -0.0384 1.0000 0.0517
-5.000 -0.3182 0.02376 0.01496 -0.0374 1.0000 0.0534
-4.750 -0.2956 0.02251 0.01335 -0.0364 1.0000 0.0548
-4.500 -0.2729 0.02173 0.01224 -0.0355 1.0000 0.0575
-4.250 -0.2497 0.02070 0.01101 -0.0347 1.0000 0.0593
-4.000 -0.2255 0.01986 0.01004 -0.0341 0.9998 0.0597
-3.750 -0.1909 0.01902 0.00906 -0.0356 0.9962 0.0602
-3.500 -0.1571 0.01832 0.00828 -0.0370 0.9925 0.0610
-3.250 -0.1233 0.01774 0.00763 -0.0384 0.9884 0.0623
-3.000 -0.0889 0.01727 0.00706 -0.0399 0.9839 0.0641
-2.750 -0.0544 0.01686 0.00658 -0.0413 0.9788 0.0668
-2.500 -0.0204 0.01652 0.00617 -0.0427 0.9739 0.0705
-2.250 0.0129 0.01615 0.00588 -0.0440 0.9685 0.0782
-2.000 0.0481 0.01576 0.00575 -0.0457 0.9637 0.1234
-1.750 0.0812 0.01550 0.00571 -0.0470 0.9570 0.1913
-1.500 0.1185 0.01531 0.00561 -0.0491 0.9525 0.2354
-1.250 0.1507 0.01515 0.00551 -0.0501 0.9448 0.2660
-1.000 0.1899 0.01480 0.00535 -0.0525 0.9391 0.3204
-0.750 0.2439 0.01302 0.00539 -0.0577 0.9353 1.0000
-0.500 0.2809 0.01294 0.00520 -0.0594 0.9258 1.0000
-0.250 0.3152 0.01289 0.00506 -0.0606 0.9147 1.0000
0.250 0.3833 0.01278 0.00484 -0.0627 0.8922 1.0000
0.500 0.4148 0.01276 0.00479 -0.0632 0.8792 1.0000
0.750 0.4439 0.01276 0.00478 -0.0631 0.8645 1.0000
1.000 0.4717 0.01278 0.00481 -0.0629 0.8490 1.0000
1.250 0.4988 0.01280 0.00485 -0.0624 0.8310 1.0000
1.500 0.5257 0.01278 0.00483 -0.0617 0.8080 1.0000
1.750 0.5520 0.01277 0.00480 -0.0608 0.7802 1.0000
2.000 0.5778 0.01278 0.00476 -0.0598 0.7435 1.0000
2.250 0.6032 0.01286 0.00475 -0.0587 0.7014 1.0000
2.500 0.6279 0.01302 0.00483 -0.0577 0.6531 1.0000
2.750 0.6515 0.01329 0.00488 -0.0563 0.5871 1.0000
3.250 0.6971 0.01424 0.00536 -0.0539 0.4997 1.0000
3.500 0.7206 0.01466 0.00576 -0.0530 0.4607 1.0000
3.750 0.7434 0.01511 0.00617 -0.0520 0.3965 1.0000
4.000 0.7627 0.01594 0.00655 -0.0506 0.3079 1.0000
4.250 0.7818 0.01698 0.00715 -0.0494 0.2355 1.0000
4.500 0.8023 0.01788 0.00778 -0.0484 0.1930 1.0000
4.750 0.8241 0.01860 0.00842 -0.0476 0.1669 1.0000
5.000 0.8472 0.01918 0.00908 -0.0469 0.1403 1.0000
5.250 0.8693 0.01990 0.00960 -0.0462 0.0874 1.0000
5.500 0.8865 0.02135 0.01062 -0.0447 0.0354 1.0000
5.750 0.9058 0.02261 0.01186 -0.0433 0.0283 1.0000
6.000 0.9263 0.02368 0.01311 -0.0420 0.0261 1.0000
6.250 0.9460 0.02484 0.01448 -0.0406 0.0242 1.0000
6.500 0.9645 0.02614 0.01601 -0.0392 0.0218 1.0000
6.750 0.9810 0.02768 0.01773 -0.0376 0.0200 1.0000
7.000 0.9964 0.02947 0.01969 -0.0358 0.0192 1.0000
7.250 1.0116 0.03165 0.02204 -0.0340 0.0185 1.0000
7.500 1.0280 0.03423 0.02479 -0.0324 0.0180 1.0000
7.750 1.0459 0.03634 0.02717 -0.0310 0.0178 1.0000
8.000 1.0624 0.03841 0.02957 -0.0295 0.0172 1.0000
8.250 1.0766 0.04062 0.03215 -0.0277 0.0165 1.0000
8.500 1.0877 0.04314 0.03506 -0.0258 0.0158 1.0000
8.750 1.0948 0.04607 0.03839 -0.0235 0.0155 1.0000
9.000 1.0973 0.04928 0.04201 -0.0209 0.0154 1.0000
9.250 1.0947 0.05263 0.04574 -0.0181 0.0154 1.0000
9.500 1.0865 0.05596 0.04950 -0.0150 0.0154 1.0000
9.750 1.0728 0.05927 0.05310 -0.0117 0.0154 1.0000
10.000 1.0568 0.06300 0.05710 -0.0095 0.0154 1.0000
10.250 1.0392 0.06727 0.06161 -0.0087 0.0155 1.0000
10.500 1.0202 0.07227 0.06684 -0.0094 0.0156 1.0000
10.750 1.0002 0.07824 0.07293 -0.0119 0.0157 1.0000
11.000 0.9794 0.08554 0.08041 -0.0164 0.0158 1.0000
11.250 0.9581 0.09455 0.08956 -0.0227 0.0160 1.0000
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Polar data table (+)
Polar graphs
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