DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DRAGONFLY CANARD (drgnfly-il) Reynolds number: 1,000,000 Max Cl/Cd: 144.64 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-drgnfly-il-1000000.txt Download as CSV file: xf-drgnfly-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 0.0531 0.08921 0.08545 -0.1204 0.5894 0.0215
-11.000 0.0551 0.08603 0.08228 -0.1217 0.5885 0.0219
-10.750 -0.1814 0.02889 0.02521 -0.1352 0.5893 0.0201
-10.500 -0.1665 0.02881 0.02516 -0.1351 0.5881 0.0203
-10.250 -0.2560 0.03548 0.03126 -0.1356 0.5889 0.0195
-10.000 -0.2832 0.03300 0.02858 -0.1296 0.5880 0.0195
-9.750 -0.3101 0.02955 0.02474 -0.1238 0.5870 0.0197
-9.500 -0.3187 0.02656 0.02146 -0.1199 0.5857 0.0200
-9.250 -0.3057 0.02555 0.02035 -0.1183 0.5838 0.0202
-9.000 -0.2877 0.02497 0.01974 -0.1172 0.5829 0.0205
-8.750 -0.2673 0.02456 0.01932 -0.1164 0.5821 0.0207
-8.500 -0.2485 0.02391 0.01862 -0.1154 0.5811 0.0210
-8.250 -0.2321 0.02289 0.01747 -0.1140 0.5801 0.0212
-8.000 -0.2154 0.02178 0.01620 -0.1125 0.5790 0.0215
-7.750 -0.1981 0.02059 0.01484 -0.1111 0.5780 0.0217
-7.500 -0.1788 0.01957 0.01366 -0.1099 0.5768 0.0220
-7.250 -0.1581 0.01864 0.01259 -0.1089 0.5757 0.0222
-7.000 -0.1364 0.01781 0.01162 -0.1081 0.5746 0.0225
-6.750 -0.1135 0.01715 0.01083 -0.1073 0.5735 0.0229
-6.500 -0.0896 0.01667 0.01025 -0.1067 0.5724 0.0232
-6.250 -0.0652 0.01633 0.00980 -0.1062 0.5711 0.0235
-6.000 -0.0423 0.01543 0.00877 -0.1056 0.5697 0.0239
-5.750 -0.0187 0.01472 0.00804 -0.1051 0.5682 0.0245
-5.500 0.0061 0.01430 0.00762 -0.1047 0.5675 0.0250
-5.250 0.0312 0.01393 0.00723 -0.1044 0.5666 0.0254
-5.000 0.0564 0.01357 0.00685 -0.1040 0.5655 0.0258
-4.750 0.0815 0.01323 0.00649 -0.1036 0.5645 0.0262
-4.500 0.1066 0.01292 0.00615 -0.1032 0.5635 0.0267
-4.250 0.1319 0.01263 0.00584 -0.1028 0.5624 0.0273
-4.000 0.1575 0.01241 0.00558 -0.1025 0.5613 0.0278
-3.750 0.1835 0.01222 0.00536 -0.1022 0.5603 0.0282
-3.500 0.2065 0.01177 0.00489 -0.1015 0.5592 0.0289
-3.250 0.2304 0.01146 0.00456 -0.1009 0.5582 0.0298
-3.000 0.2558 0.01128 0.00436 -0.1005 0.5571 0.0306
-2.750 0.2815 0.01113 0.00419 -0.1003 0.5559 0.0314
-2.500 0.3075 0.01105 0.00407 -0.1000 0.5545 0.0323
-2.250 0.3336 0.01098 0.00397 -0.0999 0.5532 0.0331
-2.000 0.3600 0.01085 0.00385 -0.0997 0.5524 0.0337
-1.750 0.3850 0.01062 0.00362 -0.0992 0.5516 0.0356
-1.500 0.4111 0.01051 0.00352 -0.0991 0.5507 0.0376
-1.250 0.4377 0.01042 0.00343 -0.0989 0.5497 0.0395
-1.000 0.4640 0.01032 0.00334 -0.0988 0.5487 0.0428
-0.750 0.4900 0.01020 0.00327 -0.0986 0.5476 0.0540
-0.500 0.5116 0.00977 0.00320 -0.0977 0.5466 0.1680
-0.250 0.5309 0.00922 0.00314 -0.0964 0.5456 0.3351
0.000 0.5492 0.00870 0.00314 -0.0949 0.5446 0.5108
0.250 0.5709 0.00847 0.00316 -0.0938 0.5436 0.5986
0.500 0.5932 0.00832 0.00318 -0.0929 0.5425 0.6640
0.750 0.6154 0.00821 0.00322 -0.0919 0.5412 0.7202
1.000 0.6361 0.00810 0.00330 -0.0905 0.5399 0.7890
1.250 0.7185 0.00803 0.00362 -0.1025 0.5385 0.9356
1.500 0.7701 0.00823 0.00381 -0.1077 0.5379 0.9606
1.750 0.8086 0.00839 0.00396 -0.1101 0.5371 0.9710
2.000 0.8489 0.00849 0.00404 -0.1130 0.5362 0.9750
2.250 0.8818 0.00859 0.00413 -0.1144 0.5351 0.9802
2.500 0.9190 0.00867 0.00420 -0.1167 0.5339 0.9829
2.750 0.9583 0.00874 0.00425 -0.1195 0.5329 0.9848
3.000 0.9963 0.00881 0.00430 -0.1221 0.5318 0.9872
3.250 1.0331 0.00888 0.00435 -0.1244 0.5307 0.9899
3.500 1.0680 0.00895 0.00441 -0.1263 0.5295 0.9927
3.750 1.1054 0.00901 0.00445 -0.1288 0.5284 0.9944
4.000 1.1433 0.00906 0.00449 -0.1314 0.5273 0.9963
4.250 1.1804 0.00915 0.00455 -0.1339 0.5260 0.9982
4.500 1.2169 0.00931 0.00468 -0.1362 0.5242 0.9997
4.750 1.2423 0.00937 0.00477 -0.1362 0.5234 1.0000
5.000 1.2643 0.00943 0.00486 -0.1354 0.5226 1.0000
5.250 1.2863 0.00950 0.00496 -0.1347 0.5215 1.0000
5.500 1.3085 0.00957 0.00506 -0.1339 0.5204 1.0000
5.750 1.3308 0.00965 0.00516 -0.1332 0.5192 1.0000
6.000 1.3531 0.00973 0.00527 -0.1326 0.5180 1.0000
6.250 1.3755 0.00981 0.00536 -0.1319 0.5167 1.0000
6.500 1.3979 0.00989 0.00546 -0.1312 0.5154 1.0000
6.750 1.4201 0.00998 0.00557 -0.1305 0.5142 1.0000
7.000 1.4422 0.01009 0.00568 -0.1298 0.5129 1.0000
7.250 1.4648 0.01023 0.00582 -0.1293 0.5114 1.0000
7.500 1.4886 0.01044 0.00603 -0.1290 0.5096 1.0000
7.750 1.5083 0.01055 0.00620 -0.1278 0.5087 1.0000
8.000 1.5278 0.01066 0.00636 -0.1266 0.5076 1.0000
8.250 1.5472 0.01077 0.00654 -0.1254 0.5062 1.0000
8.500 1.5665 0.01088 0.00669 -0.1242 0.5047 1.0000
8.750 1.5861 0.01100 0.00684 -0.1230 0.5031 1.0000
9.000 1.6056 0.01111 0.00699 -0.1219 0.5016 1.0000
9.250 1.6243 0.01123 0.00715 -0.1206 0.5000 1.0000
9.500 1.6434 0.01137 0.00731 -0.1194 0.4984 1.0000
9.750 1.6656 0.01156 0.00748 -0.1189 0.4955 1.0000
10.000 1.6790 0.01174 0.00773 -0.1166 0.4942 1.0000
10.250 1.6767 0.01181 0.00788 -0.1110 0.4910 1.0000
10.500 1.6818 0.01191 0.00803 -0.1071 0.4869 1.0000
10.750 1.6887 0.01214 0.00821 -0.1038 0.4806 1.0000
11.000 1.6897 0.01254 0.00871 -0.0998 0.4733 1.0000
11.250 1.6901 0.01324 0.00941 -0.0961 0.4634 1.0000
11.500 1.6889 0.01430 0.01046 -0.0928 0.4531 1.0000
11.750 1.6916 0.01549 0.01170 -0.0905 0.4428 1.0000
12.000 1.6908 0.01709 0.01332 -0.0882 0.4338 1.0000
12.250 1.6885 0.01897 0.01522 -0.0860 0.4257 1.0000
12.500 1.6788 0.02142 0.01769 -0.0833 0.4141 1.0000
12.750 1.6643 0.02422 0.02050 -0.0803 0.4031 1.0000
13.000 1.6460 0.02730 0.02358 -0.0770 0.3929 1.0000
13.250 1.6213 0.03087 0.02713 -0.0734 0.3799 1.0000
13.500 1.6064 0.03394 0.03019 -0.0707 0.3687 1.0000
13.750 1.5876 0.03742 0.03365 -0.0679 0.3553 1.0000
14.000 1.5683 0.04107 0.03726 -0.0653 0.3408 1.0000
14.250 1.5520 0.04456 0.04073 -0.0630 0.3270 1.0000
14.500 1.5351 0.04819 0.04432 -0.0608 0.3117 1.0000
14.750 1.5088 0.05273 0.04876 -0.0581 0.2905 1.0000
15.000 1.4924 0.05653 0.05249 -0.0562 0.2725 1.0000
15.250 1.4761 0.06040 0.05630 -0.0545 0.2550 1.0000
15.500 1.4575 0.06456 0.06035 -0.0527 0.2348 1.0000
15.750 1.4416 0.06857 0.06425 -0.0512 0.2131 1.0000
16.000 1.4195 0.07329 0.06883 -0.0496 0.1875 1.0000
16.250 1.4122 0.07656 0.07202 -0.0487 0.1708 1.0000
16.500 1.3947 0.08101 0.07634 -0.0476 0.1473 1.0000
16.750 1.3836 0.08481 0.08003 -0.0468 0.1277 1.0000
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