DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 50,000 Max Cl/Cd: 25.57 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-doa5-il-50000-n5.txt Download as CSV file: xf-doa5-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DORNIER A-5 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5175 0.10511 0.09728 -0.0593 1.0000 0.0750
-11.500 -0.5361 0.09961 0.09181 -0.0606 1.0000 0.0746
-11.250 -0.5598 0.09419 0.08640 -0.0616 1.0000 0.0742
-11.000 -0.5868 0.08927 0.08147 -0.0619 1.0000 0.0737
-10.750 -0.6170 0.08489 0.07708 -0.0612 1.0000 0.0732
-10.500 -0.6484 0.08124 0.07339 -0.0594 1.0000 0.0728
-10.250 -0.6802 0.07827 0.07037 -0.0566 1.0000 0.0724
-10.000 -0.7133 0.07590 0.06795 -0.0526 1.0000 0.0721
-9.750 -0.7424 0.07345 0.06541 -0.0486 1.0000 0.0719
-9.500 -0.7644 0.07072 0.06252 -0.0451 1.0000 0.0718
-9.250 -0.7815 0.06786 0.05946 -0.0419 1.0000 0.0718
-9.000 -0.7933 0.06500 0.05637 -0.0390 1.0000 0.0718
-8.750 -0.8007 0.06214 0.05324 -0.0364 1.0000 0.0719
-8.500 -0.8034 0.05937 0.05018 -0.0340 1.0000 0.0721
-8.250 -0.8024 0.05672 0.04722 -0.0319 1.0000 0.0725
-8.000 -0.7980 0.05422 0.04439 -0.0300 1.0000 0.0731
-7.750 -0.7913 0.05188 0.04165 -0.0282 1.0000 0.0742
-7.500 -0.7823 0.04968 0.03895 -0.0265 1.0000 0.0755
-7.250 -0.7581 0.04774 0.03696 -0.0272 0.9970 0.0772
-7.000 -0.7325 0.04610 0.03515 -0.0279 0.9938 0.0787
-6.750 -0.7076 0.04446 0.03330 -0.0281 0.9907 0.0801
-6.500 -0.6821 0.04300 0.03161 -0.0282 0.9877 0.0816
-6.250 -0.6545 0.04178 0.03015 -0.0285 0.9847 0.0842
-6.000 -0.6267 0.04074 0.02889 -0.0287 0.9815 0.0872
-5.750 -0.5999 0.03989 0.02812 -0.0285 0.9780 0.0902
-5.500 -0.5707 0.03927 0.02747 -0.0284 0.9749 0.0935
-5.250 -0.5397 0.03887 0.02695 -0.0283 0.9723 0.0972
-5.000 -0.5164 0.03837 0.02648 -0.0272 0.9685 0.1016
-4.750 -0.4922 0.03791 0.02604 -0.0267 0.9644 0.1076
-4.500 -0.4652 0.03748 0.02555 -0.0267 0.9606 0.1146
-4.250 -0.4481 0.03677 0.02492 -0.0256 0.9550 0.1220
-4.000 -0.4259 0.03610 0.02427 -0.0256 0.9504 0.1325
-3.750 -0.4060 0.03532 0.02355 -0.0253 0.9453 0.1466
-3.500 -0.3870 0.03430 0.02264 -0.0252 0.9398 0.1692
-3.250 -0.3649 0.03248 0.02137 -0.0268 0.9355 0.2309
-3.000 -0.3676 0.03233 0.02331 -0.0191 0.9287 0.5572
-2.750 -0.3452 0.03389 0.02475 -0.0163 0.9237 0.6325
-2.500 -0.3278 0.03541 0.02616 -0.0124 0.9184 0.6670
-2.250 -0.3094 0.03620 0.02678 -0.0102 0.9130 0.6906
-2.000 -0.2863 0.03741 0.02787 -0.0074 0.9087 0.7107
-1.750 -0.2715 0.03834 0.02873 -0.0035 0.9029 0.7323
-1.500 -0.2554 0.03896 0.02927 -0.0003 0.8970 0.7537
-1.250 -0.2312 0.03935 0.02954 0.0010 0.8928 0.7694
-1.000 -0.2154 0.03928 0.02939 0.0029 0.8866 0.7777
-0.750 -0.1925 0.03913 0.02911 0.0029 0.8808 0.7842
-0.500 -0.1609 0.03899 0.02881 0.0010 0.8765 0.7887
-0.250 -0.1463 0.03878 0.02854 0.0026 0.8690 0.7924
0.000 -0.1188 0.03868 0.02834 0.0017 0.8639 0.7964
0.250 -0.0940 0.03860 0.02816 0.0011 0.8587 0.8009
0.500 -0.0726 0.03848 0.02797 0.0011 0.8513 0.8052
0.750 -0.0345 0.03837 0.02778 -0.0010 0.8455 0.8089
1.000 -0.0136 0.03813 0.02749 -0.0004 0.8340 0.8139
1.250 0.0176 0.03787 0.02715 -0.0016 0.8239 0.8190
1.500 0.0515 0.03755 0.02680 -0.0027 0.8143 0.8227
1.750 0.0741 0.03738 0.02660 -0.0022 0.8037 0.8273
2.000 0.1077 0.03716 0.02636 -0.0035 0.7958 0.8323
2.250 0.1279 0.03709 0.02629 -0.0027 0.7857 0.8376
2.500 0.1586 0.03688 0.02609 -0.0033 0.7777 0.8427
2.750 0.1790 0.03684 0.02606 -0.0026 0.7670 0.8484
3.000 0.2117 0.03661 0.02585 -0.0036 0.7592 0.8531
3.500 0.2665 0.03623 0.02555 -0.0039 0.7404 0.8631
3.750 0.2837 0.03628 0.02564 -0.0028 0.7272 0.8686
4.000 0.3085 0.03609 0.02552 -0.0025 0.7161 0.8736
4.250 0.3420 0.03566 0.02515 -0.0032 0.7064 0.8786
4.500 0.3630 0.03557 0.02513 -0.0025 0.6917 0.8837
4.750 0.3890 0.03523 0.02488 -0.0021 0.6783 0.8888
5.000 0.4287 0.03429 0.02403 -0.0031 0.6692 0.8941
5.250 0.4537 0.03379 0.02361 -0.0023 0.6531 0.9001
5.500 0.4813 0.03306 0.02298 -0.0015 0.6358 0.9065
5.750 0.5093 0.03239 0.02241 -0.0009 0.6172 0.9131
6.000 0.5397 0.03170 0.02181 -0.0007 0.5979 0.9193
6.250 0.5727 0.03104 0.02123 -0.0009 0.5792 0.9259
6.500 0.6047 0.03064 0.02092 -0.0012 0.5578 0.9322
6.750 0.6358 0.03036 0.02071 -0.0016 0.5327 0.9392
7.000 0.6706 0.02998 0.02034 -0.0024 0.5043 0.9461
7.250 0.7054 0.02971 0.01997 -0.0032 0.4721 0.9543
7.500 0.7388 0.02970 0.01981 -0.0042 0.4394 0.9638
8.000 0.7825 0.03060 0.02042 -0.0035 0.3817 1.0000
8.250 0.8000 0.03139 0.02110 -0.0028 0.3561 1.0000
8.500 0.8170 0.03227 0.02186 -0.0021 0.3321 1.0000
8.750 0.8329 0.03326 0.02284 -0.0014 0.3089 1.0000
9.000 0.8492 0.03429 0.02383 -0.0008 0.2876 1.0000
9.250 0.8653 0.03534 0.02485 -0.0002 0.2682 1.0000
9.500 0.8809 0.03644 0.02592 0.0003 0.2506 1.0000
9.750 0.8965 0.03756 0.02703 0.0008 0.2351 1.0000
10.000 0.9126 0.03871 0.02812 0.0013 0.2221 1.0000
10.250 0.9302 0.03985 0.02913 0.0015 0.2110 1.0000
10.500 0.9506 0.04102 0.03032 0.0016 0.2004 1.0000
10.750 0.9735 0.04221 0.03153 0.0013 0.1909 1.0000
11.000 0.9987 0.04338 0.03270 0.0009 0.1824 1.0000
11.250 1.0232 0.04471 0.03412 0.0006 0.1748 1.0000
11.500 1.0452 0.04609 0.03559 0.0004 0.1675 1.0000
11.750 1.0695 0.04754 0.03705 0.0000 0.1610 1.0000
12.000 1.0856 0.04931 0.03904 0.0002 0.1552 1.0000
12.250 1.1119 0.05072 0.04040 -0.0004 0.1496 1.0000
12.500 1.1222 0.05283 0.04276 0.0003 0.1449 1.0000
12.750 1.1274 0.05508 0.04527 0.0012 0.1403 1.0000
13.000 1.1418 0.05691 0.04717 0.0015 0.1359 1.0000
13.250 1.1524 0.05909 0.04946 0.0019 0.1321 1.0000
13.500 1.1416 0.06232 0.05305 0.0034 0.1291 1.0000
13.750 1.1350 0.06548 0.05648 0.0043 0.1261 1.0000
14.000 1.1368 0.06813 0.05928 0.0047 0.1231 1.0000
14.250 1.1487 0.07017 0.06132 0.0048 0.1200 1.0000
14.500 1.1205 0.07536 0.06689 0.0053 0.1185 1.0000
14.750 1.0879 0.08157 0.07344 0.0047 0.1174 1.0000
15.000 1.0446 0.08984 0.08201 0.0024 0.1167 1.0000
15.250 0.9695 0.10456 0.09703 -0.0045 0.1171 1.0000
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