DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: DORNIER A-5 AIRFOIL (doa5-il) Reynolds number: 100,000 Max Cl/Cd: 41.3 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-doa5-il-100000.txt Download as CSV file: xf-doa5-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5406 0.09725 0.09252 -0.0324 1.0000 0.1967
-9.000 -0.5290 0.09593 0.09120 -0.0295 1.0000 0.2017
-8.750 -0.6267 0.08890 0.08433 -0.0317 1.0000 0.2090
-8.500 -0.5746 0.08875 0.08418 -0.0273 1.0000 0.2169
-8.250 -0.6149 0.08444 0.07996 -0.0265 1.0000 0.2233
-8.000 -0.6911 0.08006 0.07565 -0.0235 1.0000 0.2245
-7.250 -0.7740 0.04476 0.03832 -0.0231 1.0000 0.1133
-7.000 -0.7900 0.04798 0.04013 -0.0216 1.0000 0.0967
-6.750 -0.7751 0.04526 0.03719 -0.0206 1.0000 0.0961
-6.500 -0.7589 0.04293 0.03460 -0.0195 1.0000 0.0959
-6.250 -0.7416 0.04074 0.03215 -0.0185 1.0000 0.0955
-6.000 -0.7232 0.03874 0.02990 -0.0175 1.0000 0.0950
-5.750 -0.7040 0.03703 0.02795 -0.0164 1.0000 0.0949
-5.500 -0.6844 0.03557 0.02627 -0.0154 1.0000 0.0952
-5.250 -0.6645 0.03447 0.02490 -0.0143 1.0000 0.0965
-5.000 -0.6447 0.03331 0.02357 -0.0133 1.0000 0.0982
-4.750 -0.6255 0.03203 0.02235 -0.0123 1.0000 0.1004
-4.500 -0.6059 0.03117 0.02149 -0.0112 1.0000 0.1026
-4.250 -0.5863 0.03046 0.02075 -0.0100 1.0000 0.1050
-4.000 -0.5668 0.02985 0.02010 -0.0088 1.0000 0.1081
-3.750 -0.5474 0.02939 0.01956 -0.0077 1.0000 0.1120
-3.500 -0.5297 0.02863 0.01902 -0.0064 1.0000 0.1174
-3.250 -0.5112 0.02822 0.01865 -0.0052 1.0000 0.1238
-3.000 -0.4461 0.02890 0.01950 -0.0124 0.9842 0.1419
-2.750 -0.4138 0.02836 0.01917 -0.0141 0.9759 0.1655
-2.500 -0.3924 0.02587 0.01897 -0.0149 0.9697 0.5309
-2.250 -0.3798 0.02856 0.02204 -0.0083 0.9632 0.6646
-2.000 -0.3604 0.03081 0.02424 -0.0043 0.9554 0.6951
-1.750 -0.3413 0.03270 0.02610 -0.0003 0.9490 0.7157
-1.500 -0.3259 0.03391 0.02727 0.0034 0.9427 0.7330
-1.250 -0.3094 0.03491 0.02823 0.0067 0.9366 0.7503
-1.000 -0.2893 0.03565 0.02891 0.0091 0.9292 0.7656
-0.750 -0.2690 0.03604 0.02924 0.0109 0.9219 0.7787
-0.500 -0.2474 0.03633 0.02947 0.0127 0.9121 0.7927
-0.250 -0.2133 0.03668 0.02974 0.0127 0.9009 0.8077
0.000 -0.1883 0.03659 0.02959 0.0137 0.8892 0.8213
0.250 -0.1658 0.03635 0.02931 0.0150 0.8777 0.8295
0.500 -0.1172 0.03642 0.02927 0.0107 0.8708 0.8365
0.750 -0.1038 0.03597 0.02879 0.0127 0.8598 0.8407
1.000 -0.0691 0.03582 0.02859 0.0109 0.8517 0.8451
1.250 -0.0396 0.03566 0.02837 0.0096 0.8429 0.8501
1.500 -0.0080 0.03551 0.02819 0.0083 0.8354 0.8540
1.750 0.0186 0.03529 0.02795 0.0080 0.8264 0.8581
2.000 0.0543 0.03516 0.02780 0.0061 0.8191 0.8625
2.250 0.0831 0.03503 0.02763 0.0050 0.8091 0.8672
2.500 0.1139 0.03471 0.02733 0.0044 0.8003 0.8713
2.750 0.1478 0.03430 0.02692 0.0034 0.7906 0.8762
3.000 0.1754 0.03407 0.02669 0.0030 0.7795 0.8819
3.250 0.2191 0.03329 0.02594 0.0010 0.7719 0.8863
3.500 0.2427 0.03288 0.02556 0.0016 0.7590 0.8917
3.750 0.2965 0.03182 0.02452 -0.0018 0.7535 0.8964
4.000 0.3173 0.03131 0.02406 -0.0005 0.7398 0.9020
4.250 0.3710 0.03001 0.02283 -0.0035 0.7359 0.9073
4.500 0.3952 0.02937 0.02224 -0.0027 0.7217 0.9134
4.750 0.4269 0.02839 0.02133 -0.0025 0.7088 0.9188
5.000 0.4841 0.02635 0.01936 -0.0053 0.7037 0.9230
5.250 0.5166 0.02520 0.01828 -0.0051 0.6895 0.9283
5.500 0.5587 0.02377 0.01693 -0.0061 0.6762 0.9337
5.750 0.6055 0.02228 0.01550 -0.0079 0.6614 0.9391
6.000 0.6504 0.02112 0.01439 -0.0098 0.6411 0.9439
6.250 0.7012 0.02010 0.01335 -0.0128 0.6147 0.9482
6.500 0.7382 0.01963 0.01281 -0.0139 0.5806 0.9537
6.750 0.7737 0.01953 0.01258 -0.0152 0.5409 0.9592
7.000 0.8048 0.01974 0.01262 -0.0161 0.4981 0.9656
7.250 0.8350 0.02022 0.01287 -0.0171 0.4530 0.9721
7.500 0.8642 0.02102 0.01330 -0.0181 0.4067 0.9789
7.750 0.8887 0.02202 0.01404 -0.0187 0.3626 0.9885
8.000 0.9008 0.02285 0.01466 -0.0170 0.3309 1.0000
8.250 0.9072 0.02352 0.01518 -0.0142 0.3060 1.0000
8.500 0.9198 0.02428 0.01578 -0.0126 0.2840 1.0000
8.750 0.9342 0.02507 0.01645 -0.0113 0.2642 1.0000
9.000 0.9507 0.02588 0.01721 -0.0104 0.2467 1.0000
9.250 0.9707 0.02676 0.01796 -0.0101 0.2320 1.0000
9.500 0.9928 0.02769 0.01881 -0.0101 0.2186 1.0000
9.750 1.0185 0.02875 0.01983 -0.0106 0.2064 1.0000
10.000 1.0496 0.03001 0.02103 -0.0119 0.1953 1.0000
10.250 1.0920 0.03153 0.02232 -0.0150 0.1842 1.0000
10.500 1.1098 0.03266 0.02367 -0.0143 0.1765 1.0000
10.750 1.1527 0.03438 0.02525 -0.0176 0.1673 1.0000
11.000 1.1672 0.03559 0.02670 -0.0164 0.1611 1.0000
11.250 1.2163 0.03775 0.02867 -0.0208 0.1524 1.0000
11.500 1.2210 0.03892 0.03018 -0.0181 0.1482 1.0000
11.750 1.2360 0.04035 0.03178 -0.0171 0.1430 1.0000
12.000 1.2747 0.04269 0.03401 -0.0200 0.1365 1.0000
12.250 1.2714 0.04406 0.03576 -0.0163 0.1333 1.0000
12.500 1.2784 0.04567 0.03759 -0.0144 0.1293 1.0000
12.750 1.2967 0.04716 0.03908 -0.0141 0.1248 1.0000
13.000 1.3074 0.04953 0.04159 -0.0131 0.1211 1.0000
13.250 1.2959 0.05155 0.04397 -0.0092 0.1187 1.0000
13.500 1.2910 0.05371 0.04639 -0.0065 0.1159 1.0000
13.750 1.3018 0.05521 0.04794 -0.0056 0.1122 1.0000
14.000 1.3199 0.05761 0.05030 -0.0059 0.1088 1.0000
14.250 1.2951 0.06058 0.05365 -0.0019 0.1077 1.0000
14.500 1.2697 0.06414 0.05756 0.0011 0.1066 1.0000
14.750 1.2425 0.06825 0.06198 0.0034 0.1056 1.0000
15.000 1.2117 0.07304 0.06707 0.0049 0.1049 1.0000
15.250 1.1737 0.07902 0.07334 0.0054 0.1048 1.0000
15.500 1.1246 0.08705 0.08165 0.0042 0.1057 1.0000
15.750 1.0654 0.09782 0.09267 0.0003 0.1071 1.0000
16.000 1.0026 0.11183 0.10686 -0.0067 0.1087 1.0000
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