D.G.A. 1138 (dga1138-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: D.G.A. 1138 (dga1138-il) Reynolds number: 200,000 Max Cl/Cd: 69.27 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dga1138-il-200000.txt Download as CSV file: xf-dga1138-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4919 0.10302 0.09943 -0.0179 1.0000 0.0412
-9.500 -0.4938 0.09948 0.09594 -0.0219 1.0000 0.0415
-9.250 -0.4964 0.09581 0.09232 -0.0254 1.0000 0.0417
-9.000 -0.4939 0.09146 0.08799 -0.0298 1.0000 0.0418
-8.750 -0.4976 0.08489 0.08147 -0.0312 1.0000 0.0424
-8.500 -0.4927 0.08179 0.07838 -0.0280 1.0000 0.0434
-8.250 -0.4864 0.07886 0.07546 -0.0275 1.0000 0.0446
-8.000 -0.4805 0.07557 0.07218 -0.0285 1.0000 0.0459
-7.750 -0.4746 0.07188 0.06848 -0.0302 1.0000 0.0475
-7.500 -0.4676 0.06769 0.06426 -0.0328 1.0000 0.0498
-7.250 -0.4509 0.06085 0.05707 -0.0415 1.0000 0.0538
-7.000 -0.4501 0.05462 0.05081 -0.0415 1.0000 0.0551
-6.750 -0.4418 0.05378 0.05007 -0.0385 1.0000 0.0573
-6.500 -0.4309 0.05160 0.04783 -0.0376 1.0000 0.0619
-6.250 -0.4204 0.04639 0.04235 -0.0388 1.0000 0.0689
-6.000 -0.4091 0.04517 0.04114 -0.0368 1.0000 0.0730
-5.750 -0.3967 0.04221 0.03800 -0.0362 1.0000 0.0825
-5.500 -0.3828 0.04008 0.03570 -0.0354 1.0000 0.0941
-5.250 -0.3682 0.03856 0.03405 -0.0342 1.0000 0.1069
-4.750 -0.3181 0.02312 0.01657 -0.0334 1.0000 0.0639
-4.500 -0.2948 0.02131 0.01431 -0.0325 1.0000 0.0647
-4.250 -0.2700 0.01963 0.01229 -0.0318 1.0000 0.0642
-4.000 -0.2438 0.01840 0.01078 -0.0314 1.0000 0.0641
-3.750 -0.2141 0.01766 0.00980 -0.0317 0.9990 0.0659
-3.500 -0.1775 0.01680 0.00877 -0.0334 0.9966 0.0665
-3.250 -0.1405 0.01574 0.00764 -0.0352 0.9946 0.0674
-3.000 -0.1042 0.01494 0.00685 -0.0371 0.9912 0.0690
-2.750 -0.0672 0.01441 0.00635 -0.0391 0.9875 0.0722
-2.500 -0.0285 0.01404 0.00597 -0.0415 0.9844 0.0762
-2.250 0.0081 0.01370 0.00561 -0.0433 0.9791 0.0797
-2.000 0.0480 0.01332 0.00532 -0.0458 0.9739 0.0906
-1.750 0.0891 0.01286 0.00516 -0.0487 0.9693 0.1602
-1.500 0.1260 0.01255 0.00505 -0.0506 0.9620 0.2191
-1.250 0.1696 0.01213 0.00488 -0.0540 0.9578 0.2816
-1.000 0.2259 0.01015 0.00501 -0.0599 0.9585 0.9997
-0.750 0.2647 0.01004 0.00478 -0.0621 0.9510 1.0000
-0.500 0.3078 0.00985 0.00449 -0.0651 0.9451 1.0000
-0.250 0.3428 0.00973 0.00432 -0.0664 0.9361 1.0000
0.000 0.3820 0.00955 0.00410 -0.0686 0.9298 1.0000
0.250 0.4128 0.00947 0.00399 -0.0689 0.9186 1.0000
0.500 0.4436 0.00936 0.00386 -0.0690 0.9058 1.0000
0.750 0.4720 0.00927 0.00374 -0.0686 0.8906 1.0000
1.000 0.4986 0.00919 0.00363 -0.0677 0.8728 1.0000
1.250 0.5218 0.00916 0.00356 -0.0661 0.8485 1.0000
1.500 0.5455 0.00912 0.00348 -0.0646 0.8214 1.0000
1.750 0.5696 0.00911 0.00341 -0.0633 0.7924 1.0000
2.000 0.5944 0.00916 0.00340 -0.0622 0.7651 1.0000
2.250 0.6192 0.00926 0.00342 -0.0612 0.7341 1.0000
2.500 0.6436 0.00942 0.00350 -0.0601 0.6973 1.0000
2.750 0.6671 0.00963 0.00358 -0.0590 0.6452 1.0000
3.000 0.6887 0.01002 0.00365 -0.0574 0.5771 1.0000
3.250 0.7099 0.01059 0.00390 -0.0560 0.5285 1.0000
3.500 0.7316 0.01116 0.00427 -0.0547 0.4744 1.0000
3.750 0.7515 0.01179 0.00451 -0.0533 0.3624 1.0000
4.000 0.7683 0.01295 0.00500 -0.0517 0.2500 1.0000
4.250 0.7900 0.01365 0.00549 -0.0509 0.2112 1.0000
4.500 0.8127 0.01424 0.00598 -0.0501 0.1890 1.0000
4.750 0.8356 0.01479 0.00648 -0.0495 0.1630 1.0000
5.000 0.8598 0.01521 0.00684 -0.0489 0.1298 1.0000
5.250 0.8801 0.01623 0.00744 -0.0478 0.0577 1.0000
5.500 0.9007 0.01727 0.00832 -0.0465 0.0385 1.0000
5.750 0.9211 0.01832 0.00940 -0.0452 0.0327 1.0000
6.000 0.9422 0.01923 0.01049 -0.0439 0.0308 1.0000
6.250 0.9620 0.02031 0.01169 -0.0425 0.0293 1.0000
6.500 0.9811 0.02155 0.01302 -0.0410 0.0282 1.0000
6.750 1.0003 0.02296 0.01451 -0.0395 0.0275 1.0000
7.000 1.0201 0.02453 0.01617 -0.0381 0.0266 1.0000
7.250 1.0393 0.02669 0.01842 -0.0369 0.0251 1.0000
7.500 1.0596 0.02980 0.02173 -0.0358 0.0244 1.0000
7.750 1.0799 0.03225 0.02445 -0.0346 0.0245 1.0000
8.000 1.0990 0.03442 0.02690 -0.0332 0.0247 1.0000
8.250 1.1168 0.03637 0.02920 -0.0315 0.0253 1.0000
8.500 1.1246 0.04079 0.03449 -0.0278 0.0282 1.0000
8.750 1.1234 0.04653 0.04083 -0.0243 0.0310 1.0000
9.250 1.0225 0.04970 0.04537 -0.0075 0.0400 1.0000
14.000 0.8789 0.18572 0.18206 -0.0676 0.0483 1.0000
14.250 0.8849 0.18934 0.18569 -0.0690 0.0463 1.0000
14.500 0.8961 0.19212 0.18849 -0.0687 0.0444 1.0000
14.750 0.6746 0.17161 0.16824 -0.0397 0.0531 1.0000
15.000 0.6590 0.17379 0.17040 -0.0438 0.0510 1.0000
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Polar data table (+)
Polar graphs
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