D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 200,000 Max Cl/Cd: 29.27 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1182-il-200000.txt Download as CSV file: xf-dga1182-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1182
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5660 0.08381 0.07929 0.0007 0.3351 0.0346
-8.250 -0.5746 0.07804 0.07353 -0.0033 0.3338 0.0347
-8.000 -0.5863 0.07210 0.06758 -0.0079 0.3326 0.0344
-7.750 -0.5994 0.06717 0.06258 -0.0100 0.3321 0.0344
-7.500 -0.6061 0.06236 0.05762 -0.0120 0.3307 0.0350
-7.250 -0.6063 0.05862 0.05359 -0.0130 0.3285 0.0359
-7.000 -0.6013 0.05479 0.04947 -0.0131 0.3260 0.0363
-6.500 -0.6379 0.05482 0.04867 -0.0102 0.3206 0.0373
-6.250 -0.6253 0.05042 0.04430 -0.0105 0.3179 0.0389
-6.000 -0.6092 0.04742 0.04118 -0.0105 0.3154 0.0414
-5.750 -0.5896 0.04456 0.03803 -0.0102 0.3134 0.0459
-5.500 -0.5710 0.04081 0.03381 -0.0097 0.3118 0.0520
-5.250 -0.5510 0.03843 0.03132 -0.0096 0.3101 0.0573
-5.000 -0.5306 0.03611 0.02875 -0.0093 0.3085 0.0696
-4.750 -0.5088 0.03511 0.02727 -0.0088 0.3070 0.0915
-4.500 -0.4871 0.03265 0.02473 -0.0086 0.3056 0.1062
-4.250 -0.4648 0.03027 0.02231 -0.0085 0.3041 0.1225
-3.750 -0.3936 0.02171 0.01223 -0.0038 0.3012 0.0398
-3.500 -0.3645 0.02095 0.01122 -0.0030 0.3003 0.0358
-3.250 -0.3380 0.01896 0.00912 -0.0023 0.2998 0.0350
-3.000 -0.3115 0.01787 0.00791 -0.0016 0.2996 0.0370
-2.750 -0.2870 0.01635 0.00637 -0.0009 0.2988 0.0387
-2.500 -0.2615 0.01541 0.00538 -0.0003 0.2977 0.0401
-2.250 -0.2352 0.01476 0.00462 0.0001 0.2972 0.0434
-2.000 -0.2080 0.01436 0.00409 0.0004 0.2967 0.0506
-1.750 -0.1812 0.01353 0.00367 0.0006 0.2960 0.1852
-1.500 -0.1536 0.01396 0.00426 0.0008 0.2941 0.3882
-1.250 -0.1273 0.01398 0.00428 0.0011 0.2915 0.4186
-1.000 -0.1014 0.01364 0.00397 0.0013 0.2880 0.4454
-0.750 -0.0740 0.01354 0.00379 0.0014 0.2853 0.4543
-0.500 -0.0463 0.01344 0.00363 0.0014 0.2839 0.4566
-0.250 -0.0186 0.01333 0.00349 0.0014 0.2823 0.4581
0.000 0.0091 0.01326 0.00338 0.0014 0.2807 0.4593
0.250 0.0369 0.01317 0.00330 0.0014 0.2791 0.4611
0.500 0.0647 0.01310 0.00325 0.0014 0.2768 0.4628
0.750 0.0925 0.01305 0.00320 0.0014 0.2688 0.4639
1.000 0.1199 0.01311 0.00309 0.0013 0.2044 0.4647
1.250 0.1469 0.01331 0.00315 0.0013 0.1971 0.4659
1.500 0.1742 0.01347 0.00330 0.0013 0.1919 0.4671
1.750 0.2013 0.01368 0.00353 0.0014 0.1880 0.4677
2.000 0.2278 0.01407 0.00393 0.0014 0.1830 0.4687
2.250 0.2539 0.01458 0.00445 0.0015 0.1774 0.4698
2.500 0.2780 0.01582 0.00547 0.0018 0.1663 0.4711
2.750 0.3035 0.01708 0.00661 0.0019 0.1518 0.4723
3.000 0.3298 0.01818 0.00767 0.0018 0.1393 0.4733
3.250 0.3565 0.01843 0.00809 0.0019 0.1288 0.4743
3.500 0.3834 0.01835 0.00829 0.0021 0.1182 0.4756
3.750 0.4108 0.01794 0.00813 0.0022 0.1061 0.4774
4.000 0.4394 0.01708 0.00751 0.0023 0.0944 0.4796
4.250 0.4686 0.01643 0.00698 0.0023 0.0855 0.4820
4.500 0.4948 0.01702 0.00766 0.0026 0.0784 0.4842
4.750 0.5204 0.01778 0.00852 0.0030 0.0739 0.4874
5.000 0.5449 0.01910 0.00990 0.0034 0.0694 0.4912
5.250 0.5708 0.02012 0.01111 0.0038 0.0672 0.4958
5.500 0.5965 0.02163 0.01287 0.0041 0.0651 0.5019
5.750 0.6220 0.02340 0.01500 0.0045 0.0626 0.5117
6.000 0.6452 0.02325 0.01538 0.0050 0.0586 0.6584
6.250 0.6618 0.02543 0.01836 0.0071 0.0559 0.8675
6.500 0.6853 0.02802 0.02159 0.0082 0.0516 0.9002
6.750 0.7194 0.02813 0.02186 0.0064 0.0467 0.9748
7.000 0.7362 0.03300 0.02724 0.0071 0.0439 1.0000
7.250 0.7506 0.03986 0.03491 0.0087 0.0406 1.0000
7.500 0.7611 0.04601 0.04158 0.0096 0.0406 1.0000
7.750 0.7681 0.05194 0.04788 0.0101 0.0422 1.0000
8.000 0.7641 0.06272 0.05924 0.0098 0.0591 1.0000
8.250 0.7745 0.06695 0.06347 0.0098 0.0577 1.0000
8.500 0.7724 0.07609 0.07256 0.0086 0.0563 1.0000
8.750 0.6616 0.06844 0.06565 0.0099 0.0598 1.0000
9.000 0.6301 0.07723 0.07443 0.0015 0.0611 1.0000
9.250 0.6219 0.08267 0.07985 -0.0009 0.0602 1.0000
9.500 0.6271 0.08601 0.08319 0.0000 0.0584 1.0000
9.750 0.7250 0.10358 0.10056 -0.0165 0.0544 1.0000
10.000 0.6306 0.09624 0.09338 0.0032 0.0563 1.0000
10.250 0.6199 0.10234 0.09946 -0.0008 0.0562 1.0000
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Polar data table (+)
Polar graphs
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