DRAGONFLY CANARD (drgnfly-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DRAGONFLY CANARD (drgnfly-il) Reynolds number: 1,000,000 Max Cl/Cd: 149.08 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-drgnfly-il-1000000-n5.txt Download as CSV file: xf-drgnfly-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4735 0.04534 0.04120 -0.1394 0.5877 0.0140
-14.250 -0.5183 0.03758 0.03322 -0.1440 0.5870 0.0140
-14.000 -0.5381 0.03386 0.02936 -0.1448 0.5860 0.0140
-13.750 -0.5443 0.03179 0.02718 -0.1443 0.5847 0.0141
-13.500 -0.5525 0.02987 0.02515 -0.1429 0.5835 0.0142
-13.250 -0.5550 0.02848 0.02367 -0.1410 0.5828 0.0143
-13.000 -0.5575 0.02717 0.02226 -0.1385 0.5819 0.0143
-12.750 -0.5570 0.02608 0.02109 -0.1358 0.5810 0.0144
-12.500 -0.5553 0.02508 0.01999 -0.1328 0.5798 0.0145
-12.250 -0.5477 0.02444 0.01929 -0.1303 0.5785 0.0147
-12.000 -0.5428 0.02375 0.01851 -0.1272 0.5772 0.0148
-11.750 -0.5372 0.02300 0.01766 -0.1242 0.5760 0.0150
-11.500 -0.5249 0.02232 0.01687 -0.1222 0.5746 0.0151
-11.250 -0.5128 0.02151 0.01594 -0.1202 0.5734 0.0153
-11.000 -0.4985 0.02079 0.01511 -0.1185 0.5721 0.0154
-10.750 -0.4830 0.02009 0.01429 -0.1168 0.5709 0.0155
-10.500 -0.4660 0.01946 0.01355 -0.1154 0.5696 0.0157
-10.250 -0.4480 0.01887 0.01285 -0.1141 0.5683 0.0158
-10.000 -0.4284 0.01832 0.01222 -0.1130 0.5676 0.0159
-9.750 -0.4079 0.01784 0.01166 -0.1120 0.5667 0.0160
-9.500 -0.3883 0.01723 0.01097 -0.1109 0.5658 0.0162
-9.250 -0.3686 0.01662 0.01029 -0.1098 0.5648 0.0164
-9.000 -0.3469 0.01618 0.00981 -0.1089 0.5636 0.0166
-8.750 -0.3242 0.01581 0.00939 -0.1082 0.5624 0.0168
-8.500 -0.3006 0.01553 0.00907 -0.1076 0.5611 0.0170
-8.250 -0.2771 0.01520 0.00870 -0.1070 0.5598 0.0172
-8.000 -0.2532 0.01492 0.00837 -0.1064 0.5585 0.0174
-7.750 -0.2295 0.01460 0.00800 -0.1058 0.5573 0.0176
-7.500 -0.2052 0.01434 0.00769 -0.1053 0.5561 0.0179
-7.250 -0.1809 0.01409 0.00739 -0.1048 0.5549 0.0182
-7.000 -0.1568 0.01381 0.00706 -0.1043 0.5536 0.0185
-6.750 -0.1320 0.01354 0.00674 -0.1038 0.5528 0.0189
-6.500 -0.1074 0.01325 0.00642 -0.1034 0.5520 0.0191
-6.250 -0.0824 0.01299 0.00612 -0.1030 0.5512 0.0193
-6.000 -0.0572 0.01276 0.00585 -0.1026 0.5502 0.0195
-5.750 -0.0327 0.01246 0.00552 -0.1021 0.5492 0.0197
-5.500 -0.0086 0.01214 0.00518 -0.1015 0.5482 0.0202
-5.250 0.0166 0.01192 0.00495 -0.1012 0.5471 0.0205
-5.000 0.0422 0.01173 0.00474 -0.1009 0.5458 0.0208
-4.750 0.0679 0.01156 0.00454 -0.1006 0.5447 0.0212
-4.500 0.0936 0.01140 0.00436 -0.1003 0.5434 0.0216
-4.250 0.1193 0.01125 0.00418 -0.1000 0.5422 0.0221
-4.000 0.1453 0.01112 0.00403 -0.0997 0.5411 0.0227
-3.750 0.1713 0.01101 0.00389 -0.0995 0.5399 0.0232
-3.500 0.1972 0.01091 0.00375 -0.0993 0.5387 0.0235
-3.250 0.2231 0.01074 0.00358 -0.0990 0.5380 0.0239
-3.000 0.2489 0.01056 0.00340 -0.0987 0.5372 0.0246
-2.750 0.2752 0.01043 0.00328 -0.0986 0.5364 0.0252
-2.500 0.3017 0.01033 0.00318 -0.0985 0.5355 0.0260
-2.250 0.3283 0.01024 0.00308 -0.0983 0.5345 0.0267
-2.000 0.3550 0.01015 0.00299 -0.0983 0.5335 0.0275
-1.750 0.3818 0.01009 0.00292 -0.0982 0.5324 0.0283
-1.500 0.4080 0.00999 0.00282 -0.0980 0.5312 0.0297
-1.250 0.4344 0.00991 0.00274 -0.0979 0.5300 0.0312
-1.000 0.4610 0.00986 0.00269 -0.0978 0.5288 0.0326
-0.750 0.4875 0.00981 0.00264 -0.0977 0.5277 0.0349
-0.500 0.5136 0.00976 0.00260 -0.0976 0.5267 0.0400
-0.250 0.5386 0.00963 0.00257 -0.0972 0.5256 0.0708
0.000 0.5627 0.00946 0.00255 -0.0967 0.5244 0.1269
0.250 0.5864 0.00923 0.00254 -0.0962 0.5236 0.2050
0.500 0.6090 0.00892 0.00254 -0.0955 0.5228 0.3092
0.750 0.6314 0.00864 0.00254 -0.0948 0.5219 0.4106
1.000 0.6529 0.00836 0.00259 -0.0938 0.5209 0.5201
1.250 0.6736 0.00812 0.00264 -0.0926 0.5197 0.6174
1.500 0.6911 0.00785 0.00270 -0.0906 0.5187 0.7225
1.750 0.7076 0.00758 0.00277 -0.0883 0.5177 0.8242
2.000 0.7945 0.00755 0.00301 -0.1014 0.5166 0.9334
2.250 0.8410 0.00766 0.00309 -0.1058 0.5154 0.9446
2.750 0.9075 0.00787 0.00326 -0.1087 0.5130 0.9606
3.250 0.9673 0.00810 0.00344 -0.1103 0.5105 0.9721
3.500 0.9992 0.00821 0.00353 -0.1115 0.5094 0.9760
3.750 1.0269 0.00830 0.00363 -0.1118 0.5085 0.9807
4.000 1.0600 0.00839 0.00373 -0.1133 0.5074 0.9830
4.250 1.0944 0.00847 0.00382 -0.1152 0.5063 0.9848
4.500 1.1277 0.00856 0.00391 -0.1168 0.5051 0.9870
4.750 1.1600 0.00865 0.00401 -0.1182 0.5038 0.9893
5.000 1.1909 0.00875 0.00412 -0.1193 0.5024 0.9915
5.250 1.2211 0.00886 0.00423 -0.1203 0.5012 0.9934
5.500 1.2545 0.00895 0.00433 -0.1220 0.4998 0.9948
5.750 1.2880 0.00906 0.00443 -0.1237 0.4984 0.9965
6.000 1.3218 0.00917 0.00455 -0.1256 0.4971 0.9982
6.250 1.3559 0.00931 0.00468 -0.1275 0.4956 0.9996
6.500 1.3827 0.00941 0.00482 -0.1278 0.4945 1.0000
6.750 1.4040 0.00950 0.00495 -0.1269 0.4933 1.0000
7.000 1.4250 0.00961 0.00509 -0.1260 0.4919 1.0000
7.250 1.4456 0.00972 0.00524 -0.1250 0.4906 1.0000
7.500 1.4655 0.00983 0.00539 -0.1239 0.4889 1.0000
7.750 1.4848 0.00996 0.00554 -0.1226 0.4874 1.0000
8.000 1.5033 0.01010 0.00571 -0.1212 0.4859 1.0000
8.250 1.5207 0.01025 0.00588 -0.1196 0.4844 1.0000
8.500 1.5363 0.01042 0.00607 -0.1177 0.4826 1.0000
8.750 1.5476 0.01059 0.00625 -0.1148 0.4808 1.0000
9.000 1.5612 0.01072 0.00644 -0.1125 0.4795 1.0000
9.250 1.5752 0.01087 0.00664 -0.1102 0.4778 1.0000
9.500 1.5894 0.01104 0.00687 -0.1081 0.4758 1.0000
9.750 1.6032 0.01125 0.00712 -0.1060 0.4735 1.0000
10.000 1.6169 0.01150 0.00740 -0.1040 0.4714 1.0000
10.250 1.6241 0.01191 0.00781 -0.1009 0.4670 1.0000
10.500 1.6394 0.01221 0.00819 -0.0994 0.4638 1.0000
10.750 1.6466 0.01278 0.00878 -0.0968 0.4561 1.0000
11.000 1.6481 0.01370 0.00971 -0.0937 0.4451 1.0000
11.250 1.6353 0.01563 0.01160 -0.0895 0.4275 1.0000
11.500 1.6123 0.01880 0.01472 -0.0852 0.4088 1.0000
11.750 1.5842 0.02254 0.01842 -0.0810 0.3896 1.0000
12.000 1.5512 0.02665 0.02250 -0.0764 0.3722 1.0000
12.250 1.5196 0.03070 0.02651 -0.0721 0.3557 1.0000
12.500 1.4894 0.03495 0.03071 -0.0683 0.3389 1.0000
12.750 1.4605 0.03931 0.03499 -0.0649 0.3189 1.0000
13.000 1.4335 0.04369 0.03929 -0.0618 0.2972 1.0000
13.250 1.4118 0.04774 0.04326 -0.0593 0.2781 1.0000
13.500 1.3924 0.05172 0.04714 -0.0570 0.2558 1.0000
13.750 1.3765 0.05545 0.05077 -0.0550 0.2364 1.0000
14.000 1.3601 0.05936 0.05459 -0.0532 0.2142 1.0000
14.250 1.3538 0.06234 0.05750 -0.0520 0.1976 1.0000
14.500 1.3400 0.06614 0.06120 -0.0505 0.1769 1.0000
14.750 1.3198 0.07065 0.06553 -0.0489 0.1464 1.0000
15.000 1.3177 0.07342 0.06824 -0.0481 0.1332 1.0000
15.250 1.3138 0.07638 0.07113 -0.0474 0.1172 1.0000
15.500 1.3134 0.07908 0.07381 -0.0468 0.1074 1.0000
15.750 1.3061 0.08251 0.07711 -0.0460 0.0885 1.0000
16.000 1.2988 0.08599 0.08051 -0.0454 0.0708 1.0000
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