DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DRAGONFLY CANARD (drgnfly-il) Reynolds number: 500,000 Max Cl/Cd: 87.85 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-drgnfly-il-500000.txt Download as CSV file: xf-drgnfly-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.0609 0.09207 0.08764 -0.1179 0.6118 0.0309
-10.750 0.0620 0.08882 0.08441 -0.1193 0.6108 0.0321
-10.500 0.0355 0.08107 0.07674 -0.1249 0.6104 0.0337
-10.250 0.0247 0.07560 0.07131 -0.1267 0.6095 0.0340
-10.000 0.0306 0.07347 0.06920 -0.1268 0.6084 0.0343
-9.750 0.0380 0.07171 0.06745 -0.1269 0.6071 0.0347
-9.500 0.0406 0.06920 0.06495 -0.1277 0.6059 0.0350
-9.250 0.0407 0.06635 0.06212 -0.1287 0.6048 0.0354
-9.000 0.0340 0.06247 0.05826 -0.1308 0.6037 0.0358
-8.750 -0.0030 0.05493 0.05073 -0.1363 0.6030 0.0358
-8.500 -0.0278 0.05156 0.04730 -0.1347 0.6020 0.0361
-8.250 -0.0466 0.04911 0.04477 -0.1318 0.6011 0.0366
-8.000 -0.0577 0.04629 0.04182 -0.1296 0.6000 0.0374
-7.750 -0.1004 0.02837 0.02358 -0.1178 0.5980 0.0407
-7.500 -0.0833 0.02657 0.02185 -0.1176 0.5970 0.0412
-7.250 -0.0698 0.02512 0.02040 -0.1167 0.5958 0.0418
-7.000 -0.0568 0.02367 0.01890 -0.1157 0.5946 0.0425
-6.750 -0.0456 0.02200 0.01713 -0.1143 0.5934 0.0437
-6.500 -0.0520 0.01924 0.01374 -0.1097 0.5923 0.0482
-6.250 -0.0512 0.02500 0.01831 -0.1096 0.5929 0.0333
-6.000 -0.0324 0.02322 0.01633 -0.1083 0.5917 0.0330
-5.750 -0.0106 0.02247 0.01538 -0.1073 0.5905 0.0334
-5.500 0.0119 0.02195 0.01465 -0.1064 0.5893 0.0337
-5.250 0.0355 0.02065 0.01319 -0.1059 0.5880 0.0338
-5.000 0.0603 0.01940 0.01180 -0.1055 0.5869 0.0340
-4.750 0.0858 0.01831 0.01062 -0.1053 0.5858 0.0343
-4.500 0.1112 0.01761 0.00987 -0.1051 0.5847 0.0349
-4.250 0.1360 0.01720 0.00944 -0.1048 0.5834 0.0356
-4.000 0.1605 0.01679 0.00904 -0.1043 0.5825 0.0364
-3.750 0.1851 0.01647 0.00872 -0.1038 0.5814 0.0374
-3.500 0.2094 0.01615 0.00840 -0.1033 0.5803 0.0384
-3.250 0.2336 0.01585 0.00808 -0.1027 0.5791 0.0391
-3.000 0.2578 0.01560 0.00781 -0.1022 0.5779 0.0397
-2.750 0.2813 0.01528 0.00747 -0.1015 0.5767 0.0405
-2.500 0.3039 0.01490 0.00709 -0.1006 0.5755 0.0421
-2.250 0.3286 0.01468 0.00687 -0.1002 0.5742 0.0437
-2.000 0.3541 0.01452 0.00668 -0.0999 0.5731 0.0458
-1.750 0.3801 0.01440 0.00651 -0.0996 0.5720 0.0476
-1.500 0.4051 0.01420 0.00630 -0.0993 0.5711 0.0515
-1.250 0.4314 0.01413 0.00620 -0.0991 0.5701 0.0568
-1.000 0.4553 0.01396 0.00617 -0.0986 0.5690 0.0962
-0.750 0.4690 0.01314 0.00621 -0.0966 0.5680 0.3425
-0.500 0.4824 0.01255 0.00629 -0.0941 0.5670 0.5458
-0.250 0.5006 0.01234 0.00640 -0.0923 0.5660 0.6371
0.000 0.5189 0.01218 0.00651 -0.0905 0.5647 0.7156
0.250 0.5391 0.01201 0.00662 -0.0889 0.5633 0.7946
0.500 0.6142 0.01196 0.00685 -0.0990 0.5620 0.9083
0.750 0.6814 0.01227 0.00714 -0.1071 0.5608 0.9544
1.000 0.7321 0.01255 0.00737 -0.1119 0.5597 0.9697
1.250 0.7789 0.01270 0.00745 -0.1161 0.5587 0.9753
1.500 0.8160 0.01283 0.00753 -0.1184 0.5577 0.9819
1.750 0.8595 0.01289 0.00752 -0.1221 0.5567 0.9849
2.000 0.9011 0.01297 0.00753 -0.1253 0.5558 0.9888
2.250 0.9406 0.01309 0.00759 -0.1282 0.5547 0.9929
2.500 0.9816 0.01332 0.00776 -0.1315 0.5534 0.9960
2.750 1.0216 0.01340 0.00787 -0.1347 0.5525 0.9995
3.000 1.0432 0.01354 0.00804 -0.1340 0.5513 1.0000
3.250 1.0615 0.01371 0.00823 -0.1327 0.5500 1.0000
3.500 1.0805 0.01386 0.00841 -0.1314 0.5485 1.0000
3.750 1.1003 0.01403 0.00858 -0.1303 0.5472 1.0000
4.000 1.1208 0.01419 0.00875 -0.1293 0.5460 1.0000
4.250 1.1420 0.01432 0.00889 -0.1284 0.5448 1.0000
4.500 1.1644 0.01441 0.00898 -0.1278 0.5436 1.0000
4.750 1.1879 0.01449 0.00905 -0.1273 0.5425 1.0000
5.000 1.2119 0.01460 0.00913 -0.1269 0.5415 1.0000
5.250 1.2365 0.01473 0.00925 -0.1267 0.5405 1.0000
5.500 1.2617 0.01492 0.00942 -0.1266 0.5394 1.0000
5.750 1.2815 0.01523 0.00976 -0.1256 0.5380 1.0000
6.000 1.2969 0.01550 0.01011 -0.1237 0.5366 1.0000
6.250 1.3122 0.01580 0.01048 -0.1218 0.5351 1.0000
6.500 1.3288 0.01606 0.01079 -0.1202 0.5334 1.0000
6.750 1.3470 0.01626 0.01103 -0.1188 0.5318 1.0000
7.000 1.3667 0.01643 0.01123 -0.1177 0.5304 1.0000
7.250 1.3881 0.01656 0.01139 -0.1169 0.5291 1.0000
7.500 1.4119 0.01663 0.01147 -0.1166 0.5279 1.0000
7.750 1.4376 0.01670 0.01155 -0.1166 0.5268 1.0000
8.000 1.4649 0.01678 0.01162 -0.1170 0.5256 1.0000
8.250 1.4925 0.01699 0.01183 -0.1175 0.5244 1.0000
8.500 1.5007 0.01742 0.01236 -0.1144 0.5227 1.0000
8.750 1.5033 0.01789 0.01295 -0.1103 0.5204 1.0000
9.000 1.5109 0.01825 0.01339 -0.1072 0.5182 1.0000
9.250 1.5232 0.01853 0.01372 -0.1049 0.5164 1.0000
9.500 1.5402 0.01866 0.01389 -0.1034 0.5147 1.0000
9.750 1.5638 0.01867 0.01393 -0.1031 0.5133 1.0000
10.000 1.5933 0.01864 0.01392 -0.1038 0.5120 1.0000
10.250 1.6276 0.01863 0.01391 -0.1055 0.5107 1.0000
10.500 1.6349 0.01905 0.01440 -0.1024 0.5087 1.0000
10.750 1.5916 0.02029 0.01579 -0.0912 0.5049 1.0000
11.000 1.5883 0.02109 0.01667 -0.0873 0.5019 1.0000
11.250 1.6108 0.02111 0.01673 -0.0870 0.4998 1.0000
11.500 1.6534 0.02029 0.01590 -0.0892 0.4977 1.0000
11.750 1.6492 0.02099 0.01666 -0.0854 0.4926 1.0000
12.000 1.6344 0.02240 0.01815 -0.0810 0.4862 1.0000
12.250 1.6424 0.02285 0.01857 -0.0794 0.4782 1.0000
12.500 1.6323 0.02473 0.02047 -0.0766 0.4684 1.0000
12.750 1.5964 0.02894 0.02479 -0.0723 0.4593 1.0000
13.000 1.5924 0.03093 0.02677 -0.0704 0.4498 1.0000
13.250 1.5761 0.03402 0.02992 -0.0678 0.4408 1.0000
13.500 1.5560 0.03761 0.03356 -0.0651 0.4311 1.0000
13.750 1.5698 0.03840 0.03432 -0.0645 0.4238 1.0000
14.000 1.5509 0.04210 0.03808 -0.0622 0.4127 1.0000
14.250 1.5473 0.04455 0.04057 -0.0607 0.4047 1.0000
14.500 1.5471 0.04665 0.04265 -0.0595 0.3935 1.0000
14.750 1.5382 0.04958 0.04554 -0.0578 0.3787 1.0000
15.000 1.5347 0.05208 0.04803 -0.0565 0.3676 1.0000
15.250 1.5283 0.05490 0.05083 -0.0551 0.3539 1.0000
15.500 1.5208 0.05788 0.05379 -0.0538 0.3404 1.0000
15.750 1.5091 0.06126 0.05707 -0.0523 0.3225 1.0000
16.000 1.4925 0.06525 0.06098 -0.0507 0.3013 1.0000
16.250 1.4818 0.06873 0.06441 -0.0495 0.2854 1.0000
16.500 1.4607 0.07331 0.06886 -0.0480 0.2623 1.0000
16.750 1.4457 0.07742 0.07289 -0.0468 0.2430 1.0000
17.000 1.4240 0.08232 0.07765 -0.0456 0.2202 1.0000
17.250 1.4099 0.08646 0.08171 -0.0448 0.1998 1.0000
17.500 1.3908 0.09129 0.08641 -0.0439 0.1778 1.0000
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