DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DRAGONFLY CANARD (drgnfly-il) Reynolds number: 500,000 Max Cl/Cd: 104.74 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-drgnfly-il-500000-n5.txt Download as CSV file: xf-drgnfly-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.0070 0.08840 0.08377 -0.1160 0.5865 0.0169
-11.250 0.0063 0.08479 0.08016 -0.1174 0.5857 0.0171
-11.000 -0.0020 0.07993 0.07532 -0.1193 0.5849 0.0171
-10.750 -0.0064 0.07597 0.07136 -0.1210 0.5841 0.0174
-10.500 -0.2390 0.03908 0.03425 -0.1375 0.5856 0.0176
-10.250 -0.2763 0.03559 0.03052 -0.1322 0.5847 0.0177
-10.000 -0.3005 0.03299 0.02765 -0.1268 0.5838 0.0179
-9.750 -0.3090 0.03057 0.02495 -0.1232 0.5830 0.0181
-9.500 -0.3107 0.02833 0.02242 -0.1200 0.5820 0.0184
-9.250 -0.3060 0.02641 0.02022 -0.1174 0.5811 0.0188
-9.000 -0.2958 0.02485 0.01840 -0.1153 0.5800 0.0190
-8.750 -0.2821 0.02356 0.01687 -0.1136 0.5788 0.0193
-8.500 -0.2652 0.02258 0.01566 -0.1122 0.5776 0.0195
-8.250 -0.2473 0.02157 0.01451 -0.1109 0.5765 0.0198
-8.000 -0.2271 0.02083 0.01370 -0.1100 0.5752 0.0200
-7.750 -0.2056 0.02030 0.01309 -0.1093 0.5740 0.0203
-7.500 -0.1832 0.01987 0.01261 -0.1086 0.5727 0.0206
-7.250 -0.1606 0.01941 0.01206 -0.1080 0.5715 0.0210
-7.000 -0.1379 0.01890 0.01144 -0.1073 0.5703 0.0213
-6.750 -0.1149 0.01839 0.01082 -0.1067 0.5691 0.0217
-6.500 -0.0916 0.01787 0.01020 -0.1061 0.5681 0.0221
-6.250 -0.0679 0.01736 0.00962 -0.1055 0.5672 0.0225
-6.000 -0.0439 0.01689 0.00908 -0.1050 0.5661 0.0229
-5.750 -0.0197 0.01648 0.00859 -0.1045 0.5650 0.0232
-5.500 0.0049 0.01613 0.00818 -0.1040 0.5639 0.0236
-5.250 0.0283 0.01563 0.00765 -0.1034 0.5628 0.0240
-5.000 0.0520 0.01524 0.00724 -0.1028 0.5616 0.0244
-4.750 0.0765 0.01495 0.00694 -0.1024 0.5605 0.0249
-4.500 0.1012 0.01470 0.00667 -0.1020 0.5594 0.0256
-4.250 0.1259 0.01445 0.00639 -0.1015 0.5582 0.0263
-4.000 0.1506 0.01421 0.00610 -0.1011 0.5571 0.0269
-3.750 0.1752 0.01397 0.00582 -0.1006 0.5559 0.0275
-3.500 0.2002 0.01378 0.00558 -0.1002 0.5548 0.0280
-3.250 0.2249 0.01358 0.00533 -0.0997 0.5538 0.0285
-3.000 0.2490 0.01333 0.00508 -0.0992 0.5528 0.0293
-2.750 0.2740 0.01315 0.00491 -0.0988 0.5519 0.0302
-2.500 0.2994 0.01302 0.00479 -0.0985 0.5509 0.0315
-2.250 0.3249 0.01290 0.00466 -0.0982 0.5498 0.0327
-2.000 0.3506 0.01280 0.00454 -0.0980 0.5487 0.0336
-1.750 0.3758 0.01266 0.00440 -0.0976 0.5476 0.0352
-1.500 0.4014 0.01256 0.00430 -0.0974 0.5466 0.0372
-1.250 0.4272 0.01248 0.00421 -0.0971 0.5454 0.0397
-1.000 0.4528 0.01239 0.00414 -0.0969 0.5443 0.0453
-0.750 0.4775 0.01222 0.00407 -0.0965 0.5431 0.0700
-0.500 0.5012 0.01199 0.00400 -0.0960 0.5420 0.1275
-0.250 0.5242 0.01171 0.00396 -0.0954 0.5410 0.2111
0.000 0.5444 0.01126 0.00393 -0.0943 0.5401 0.3525
0.250 0.5638 0.01088 0.00396 -0.0930 0.5391 0.4970
0.500 0.5843 0.01067 0.00403 -0.0918 0.5382 0.5873
0.750 0.6032 0.01046 0.00412 -0.0901 0.5373 0.6725
1.000 0.6193 0.01011 0.00424 -0.0877 0.5363 0.8000
1.500 0.7677 0.01030 0.00469 -0.1078 0.5338 0.9430
2.000 0.8315 0.01055 0.00489 -0.1101 0.5314 0.9618
2.250 0.8615 0.01067 0.00499 -0.1109 0.5303 0.9698
2.500 0.8970 0.01079 0.00507 -0.1129 0.5293 0.9745
2.750 0.9281 0.01091 0.00517 -0.1139 0.5282 0.9804
3.000 0.9633 0.01101 0.00524 -0.1159 0.5271 0.9839
3.250 0.9990 0.01110 0.00530 -0.1180 0.5260 0.9871
3.500 1.0333 0.01122 0.00538 -0.1198 0.5249 0.9906
3.750 1.0668 0.01136 0.00550 -0.1214 0.5239 0.9935
4.000 1.1019 0.01147 0.00563 -0.1235 0.5228 0.9962
4.250 1.1368 0.01158 0.00577 -0.1256 0.5216 0.9988
4.500 1.1665 0.01170 0.00592 -0.1265 0.5203 1.0000
4.750 1.1871 0.01183 0.00607 -0.1255 0.5189 1.0000
5.000 1.2077 0.01196 0.00621 -0.1245 0.5176 1.0000
5.250 1.2284 0.01209 0.00636 -0.1235 0.5163 1.0000
5.500 1.2490 0.01221 0.00650 -0.1225 0.5150 1.0000
5.750 1.2696 0.01234 0.00664 -0.1215 0.5137 1.0000
6.000 1.2905 0.01246 0.00678 -0.1205 0.5126 1.0000
6.250 1.3116 0.01259 0.00691 -0.1196 0.5114 1.0000
6.500 1.3333 0.01273 0.00704 -0.1188 0.5101 1.0000
6.750 1.3523 0.01292 0.00726 -0.1176 0.5089 1.0000
7.000 1.3691 0.01312 0.00753 -0.1159 0.5075 1.0000
7.250 1.3855 0.01332 0.00779 -0.1142 0.5059 1.0000
7.500 1.4018 0.01353 0.00805 -0.1124 0.5043 1.0000
7.750 1.4177 0.01373 0.00829 -0.1106 0.5026 1.0000
8.000 1.4334 0.01393 0.00854 -0.1088 0.5011 1.0000
8.250 1.4457 0.01411 0.00875 -0.1062 0.4995 1.0000
8.500 1.4594 0.01427 0.00893 -0.1040 0.4980 1.0000
8.750 1.4758 0.01444 0.00912 -0.1023 0.4966 1.0000
9.000 1.4934 0.01464 0.00934 -0.1009 0.4951 1.0000
9.250 1.4980 0.01505 0.00985 -0.0973 0.4932 1.0000
9.500 1.5052 0.01549 0.01038 -0.0944 0.4910 1.0000
9.750 1.5140 0.01597 0.01092 -0.0920 0.4887 1.0000
10.000 1.5244 0.01646 0.01148 -0.0899 0.4865 1.0000
10.250 1.5375 0.01692 0.01198 -0.0883 0.4843 1.0000
10.500 1.5543 0.01729 0.01237 -0.0874 0.4824 1.0000
10.750 1.5677 0.01783 0.01297 -0.0860 0.4803 1.0000
11.000 1.5641 0.01924 0.01451 -0.0830 0.4769 1.0000
11.250 1.5645 0.02066 0.01602 -0.0808 0.4731 1.0000
11.500 1.5736 0.02164 0.01705 -0.0795 0.4698 1.0000
11.750 1.5806 0.02279 0.01822 -0.0781 0.4651 1.0000
12.000 1.5632 0.02575 0.02131 -0.0750 0.4586 1.0000
12.250 1.5655 0.02729 0.02284 -0.0735 0.4510 1.0000
12.500 1.5464 0.03049 0.02607 -0.0705 0.4396 1.0000
12.750 1.5242 0.03405 0.02963 -0.0674 0.4257 1.0000
13.000 1.5080 0.03727 0.03282 -0.0648 0.4105 1.0000
13.250 1.4859 0.04111 0.03660 -0.0621 0.3896 1.0000
13.500 1.4746 0.04412 0.03954 -0.0600 0.3733 1.0000
13.750 1.4580 0.04768 0.04300 -0.0578 0.3543 1.0000
14.000 1.4386 0.05159 0.04681 -0.0556 0.3327 1.0000
14.250 1.4275 0.05487 0.05002 -0.0539 0.3161 1.0000
14.500 1.4152 0.05834 0.05343 -0.0523 0.2987 1.0000
14.750 1.3959 0.06256 0.05754 -0.0505 0.2778 1.0000
15.000 1.3814 0.06643 0.06133 -0.0490 0.2575 1.0000
15.250 1.3692 0.07016 0.06497 -0.0478 0.2390 1.0000
15.500 1.3551 0.07414 0.06886 -0.0466 0.2202 1.0000
15.750 1.3439 0.07789 0.07253 -0.0456 0.2002 1.0000
16.000 1.3242 0.08267 0.07715 -0.0444 0.1743 1.0000
16.250 1.3190 0.08590 0.08035 -0.0438 0.1601 1.0000
16.500 1.3044 0.09026 0.08457 -0.0431 0.1368 1.0000
16.750 1.3003 0.09348 0.08774 -0.0427 0.1233 1.0000
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