DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DRAGONFLY CANARD (drgnfly-il) Reynolds number: 200,000 Max Cl/Cd: 45.83 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-drgnfly-il-200000-n5.txt Download as CSV file: xf-drgnfly-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DRAGONFLY CANARD
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 0.0318 0.10944 0.10358 -0.1071 0.6191 0.0380
-11.750 0.0351 0.10635 0.10048 -0.1084 0.6181 0.0383
-11.500 0.0136 0.09884 0.09301 -0.1127 0.6177 0.0337
-11.250 0.0212 0.09618 0.09033 -0.1133 0.6166 0.0335
-11.000 0.0323 0.09448 0.08861 -0.1134 0.6154 0.0346
-10.750 0.0323 0.09089 0.08503 -0.1149 0.6145 0.0346
-10.250 0.0021 0.07718 0.07142 -0.1204 0.6128 0.0282
-10.000 -0.0005 0.07352 0.06780 -0.1219 0.6116 0.0281
-9.750 -0.0102 0.06852 0.06286 -0.1243 0.6106 0.0280
-9.500 -0.0292 0.06132 0.05571 -0.1290 0.6095 0.0277
-9.250 -0.0653 0.05402 0.04835 -0.1333 0.6086 0.0274
-9.000 -0.0922 0.05023 0.04445 -0.1321 0.6074 0.0272
-8.750 -0.1181 0.04739 0.04147 -0.1284 0.6063 0.0271
-8.500 -0.1392 0.04378 0.03760 -0.1251 0.6052 0.0271
-8.250 -0.1505 0.04057 0.03406 -0.1220 0.6042 0.0273
-8.000 -0.1582 0.03741 0.03044 -0.1186 0.6031 0.0278
-7.750 -0.1583 0.03492 0.02743 -0.1155 0.6021 0.0283
-7.500 -0.1469 0.03315 0.02546 -0.1139 0.6011 0.0286
-7.250 -0.1324 0.03169 0.02378 -0.1125 0.6000 0.0289
-7.000 -0.1158 0.03042 0.02230 -0.1113 0.5990 0.0292
-6.750 -0.0988 0.02931 0.02105 -0.1100 0.5973 0.0295
-6.500 -0.0805 0.02827 0.01986 -0.1088 0.5957 0.0299
-6.250 -0.0612 0.02728 0.01871 -0.1077 0.5941 0.0304
-6.000 -0.0408 0.02634 0.01760 -0.1068 0.5927 0.0309
-5.750 -0.0193 0.02548 0.01655 -0.1059 0.5913 0.0314
-5.500 0.0031 0.02478 0.01567 -0.1051 0.5900 0.0324
-5.250 0.0263 0.02415 0.01484 -0.1045 0.5888 0.0333
-5.000 0.0501 0.02347 0.01401 -0.1039 0.5877 0.0339
-4.750 0.0741 0.02271 0.01322 -0.1035 0.5867 0.0345
-4.500 0.0983 0.02216 0.01262 -0.1031 0.5857 0.0352
-4.250 0.1226 0.02167 0.01208 -0.1027 0.5847 0.0360
-4.000 0.1471 0.02124 0.01158 -0.1022 0.5838 0.0369
-3.750 0.1689 0.02095 0.01128 -0.1013 0.5823 0.0379
-3.500 0.1904 0.02076 0.01108 -0.1004 0.5805 0.0393
-3.250 0.2116 0.02050 0.01083 -0.0994 0.5789 0.0405
-3.000 0.2325 0.02023 0.01059 -0.0985 0.5774 0.0418
-2.750 0.2543 0.02004 0.01040 -0.0976 0.5761 0.0431
-2.500 0.2767 0.01988 0.01020 -0.0968 0.5748 0.0448
-2.250 0.2996 0.01974 0.01002 -0.0960 0.5736 0.0467
-2.000 0.3226 0.01957 0.00983 -0.0954 0.5725 0.0495
-1.750 0.3465 0.01945 0.00968 -0.0948 0.5715 0.0542
-1.500 0.3705 0.01929 0.00952 -0.0943 0.5706 0.0611
-1.250 0.3947 0.01909 0.00935 -0.0938 0.5697 0.0798
-1.000 0.4171 0.01871 0.00920 -0.0931 0.5688 0.1501
-0.750 0.4322 0.01831 0.00932 -0.0913 0.5673 0.2886
-0.500 0.4405 0.01799 0.00969 -0.0882 0.5654 0.4625
-0.250 0.4524 0.01791 0.01004 -0.0855 0.5636 0.5807
0.000 0.4668 0.01783 0.01035 -0.0830 0.5620 0.6825
0.250 0.5988 0.01784 0.01095 -0.1035 0.5611 0.9299
0.500 0.6350 0.01815 0.01118 -0.1055 0.5598 0.9537
0.750 0.6725 0.01836 0.01130 -0.1078 0.5586 0.9651
1.000 0.7100 0.01853 0.01137 -0.1103 0.5574 0.9745
1.250 0.7476 0.01865 0.01139 -0.1127 0.5564 0.9832
1.500 0.7877 0.01875 0.01140 -0.1157 0.5555 0.9897
1.750 0.8275 0.01886 0.01143 -0.1186 0.5547 0.9956
2.000 0.8673 0.01896 0.01143 -0.1216 0.5540 1.0000
2.250 0.8831 0.01927 0.01172 -0.1199 0.5528 1.0000
2.500 0.8815 0.02016 0.01272 -0.1154 0.5500 1.0000
2.750 0.8870 0.02079 0.01339 -0.1121 0.5475 1.0000
3.000 0.8976 0.02125 0.01385 -0.1095 0.5456 1.0000
3.250 0.9109 0.02163 0.01422 -0.1074 0.5441 1.0000
3.500 0.9266 0.02194 0.01450 -0.1056 0.5429 1.0000
3.750 0.9449 0.02216 0.01469 -0.1043 0.5418 1.0000
4.000 0.9661 0.02228 0.01477 -0.1034 0.5408 1.0000
4.250 0.9891 0.02237 0.01482 -0.1028 0.5399 1.0000
4.500 1.0143 0.02242 0.01483 -0.1026 0.5392 1.0000
5.000 0.8844 0.02835 0.02104 -0.0765 0.5263 1.0000
5.250 0.9086 0.02841 0.02107 -0.0762 0.5256 1.0000
5.500 0.9341 0.02842 0.02106 -0.0760 0.5250 1.0000
5.750 0.9615 0.02834 0.02095 -0.0760 0.5245 1.0000
6.750 0.7611 0.05149 0.04439 -0.0548 0.4766 1.0000
7.000 0.8034 0.04996 0.04281 -0.0555 0.4794 1.0000
7.250 0.8369 0.04918 0.04202 -0.0559 0.4805 1.0000
8.250 0.8300 0.05875 0.05170 -0.0502 0.4563 1.0000
8.500 0.8524 0.05894 0.05190 -0.0500 0.4551 1.0000
8.750 0.8752 0.05911 0.05207 -0.0498 0.4542 1.0000
9.000 0.8985 0.05921 0.05219 -0.0497 0.4535 1.0000
9.250 0.9229 0.05920 0.05220 -0.0496 0.4529 1.0000
10.250 0.9227 0.06897 0.06214 -0.0456 0.4282 1.0000
10.500 0.9438 0.06927 0.06247 -0.0454 0.4269 1.0000
10.750 0.9667 0.06935 0.06258 -0.0453 0.4259 1.0000
11.000 0.9906 0.06928 0.06256 -0.0453 0.4251 1.0000
11.250 1.0147 0.06921 0.06252 -0.0452 0.4244 1.0000
12.250 1.0212 0.07891 0.07246 -0.0425 0.3998 1.0000
12.500 1.0425 0.07909 0.07269 -0.0424 0.3984 1.0000
12.750 1.0655 0.07906 0.07272 -0.0423 0.3973 1.0000
13.000 1.0892 0.07892 0.07264 -0.0423 0.3965 1.0000
13.250 1.1140 0.07864 0.07243 -0.0423 0.3958 1.0000
16.250 1.2560 0.09341 0.08805 -0.0398 0.3260 1.0000
16.500 1.2723 0.09403 0.08868 -0.0398 0.3122 1.0000
16.750 1.3016 0.09291 0.08746 -0.0398 0.2940 1.0000
17.000 1.3108 0.09434 0.08881 -0.0396 0.2724 1.0000
17.250 1.3196 0.09569 0.08996 -0.0393 0.2458 1.0000
17.500 1.3167 0.09854 0.09263 -0.0389 0.2205 1.0000
17.750 1.3073 0.10230 0.09620 -0.0385 0.1946 1.0000
18.000 1.3005 0.10587 0.09968 -0.0384 0.1753 1.0000
18.250 1.2891 0.11008 0.10374 -0.0383 0.1538 1.0000
18.500 1.2801 0.11404 0.10761 -0.0384 0.1355 1.0000
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Polar data table (+)
Polar graphs
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