Falcon (falcon-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.57 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-falcon-il-1000000.txt Download as CSV file: xf-falcon-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: Falcon
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
------ -------- --------- --------- -------- -------- --------
-17.000 -1.1009 0.07843 0.07562 -0.0311 1.0000 0.0116
-16.750 -1.1335 0.06886 0.06585 -0.0368 1.0000 0.0116
-16.500 -1.1541 0.06173 0.05858 -0.0409 1.0000 0.0116
-16.250 -1.1706 0.05568 0.05238 -0.0442 1.0000 0.0117
-16.000 -1.1830 0.05062 0.04718 -0.0467 1.0000 0.0117
-15.750 -1.1903 0.04659 0.04303 -0.0482 1.0000 0.0118
-15.500 -1.1957 0.04312 0.03944 -0.0491 1.0000 0.0119
-15.250 -1.1988 0.04019 0.03640 -0.0493 1.0000 0.0120
-15.000 -1.1990 0.03778 0.03390 -0.0491 1.0000 0.0121
-14.750 -1.1998 0.03550 0.03151 -0.0483 1.0000 0.0123
-14.500 -1.1985 0.03358 0.02949 -0.0471 1.0000 0.0124
-14.250 -1.1953 0.03195 0.02776 -0.0457 1.0000 0.0126
-14.000 -1.1928 0.03039 0.02609 -0.0438 1.0000 0.0127
-13.750 -1.1883 0.02908 0.02468 -0.0417 1.0000 0.0129
-13.500 -1.1836 0.02789 0.02339 -0.0393 1.0000 0.0131
-13.250 -1.1768 0.02693 0.02234 -0.0367 1.0000 0.0133
-13.000 -1.1700 0.02605 0.02137 -0.0338 1.0000 0.0134
-12.750 -1.1624 0.02532 0.02056 -0.0308 1.0000 0.0135
-12.500 -1.1538 0.02464 0.01980 -0.0278 1.0000 0.0137
-12.250 -1.1506 0.02312 0.01815 -0.0243 1.0000 0.0140
-12.000 -1.1421 0.02194 0.01689 -0.0215 1.0000 0.0143
-11.750 -1.1276 0.02117 0.01607 -0.0195 1.0000 0.0147
-11.500 -1.1108 0.02054 0.01540 -0.0178 1.0000 0.0150
-11.250 -1.0927 0.01999 0.01480 -0.0163 1.0000 0.0153
-11.000 -1.0741 0.01945 0.01422 -0.0148 1.0000 0.0157
-10.750 -1.0549 0.01894 0.01366 -0.0134 1.0000 0.0162
-10.500 -1.0349 0.01848 0.01315 -0.0121 1.0000 0.0166
-10.250 -1.0148 0.01803 0.01264 -0.0108 1.0000 0.0169
-10.000 -0.9945 0.01759 0.01215 -0.0094 1.0000 0.0172
-9.750 -0.9815 0.01651 0.01100 -0.0069 1.0000 0.0179
-9.500 -0.9631 0.01598 0.01045 -0.0053 1.0000 0.0184
-9.250 -0.9441 0.01557 0.01002 -0.0036 1.0000 0.0189
-9.000 -0.9267 0.01522 0.00965 -0.0017 1.0000 0.0195
-8.750 -0.8975 0.01479 0.00919 -0.0022 0.9991 0.0202
-8.500 -0.8641 0.01438 0.00874 -0.0036 0.9974 0.0208
-8.250 -0.8322 0.01382 0.00813 -0.0047 0.9946 0.0216
-8.000 -0.8084 0.01319 0.00749 -0.0041 0.9790 0.0227
-7.750 -0.7761 0.01279 0.00708 -0.0052 0.9739 0.0238
-7.500 -0.7413 0.01240 0.00666 -0.0068 0.9700 0.0249
-7.250 -0.7037 0.01205 0.00628 -0.0090 0.9668 0.0258
-7.000 -0.6665 0.01143 0.00564 -0.0113 0.9629 0.0279
-6.750 -0.6242 0.01107 0.00528 -0.0146 0.9595 0.0300
-6.500 -0.5786 0.01066 0.00485 -0.0188 0.9559 0.0325
-6.250 -0.5362 0.01026 0.00446 -0.0222 0.9492 0.0362
-5.750 -0.4656 0.00972 0.00388 -0.0257 0.9291 0.0453
-5.500 -0.4391 0.00947 0.00364 -0.0254 0.9168 0.0524
-5.250 -0.4133 0.00926 0.00344 -0.0249 0.9039 0.0603
-5.000 -0.3878 0.00908 0.00326 -0.0243 0.8899 0.0692
-4.750 -0.3626 0.00893 0.00310 -0.0237 0.8739 0.0776
-4.500 -0.3379 0.00877 0.00294 -0.0229 0.8558 0.0879
-4.250 -0.3133 0.00865 0.00278 -0.0221 0.8348 0.0970
-4.000 -0.2885 0.00859 0.00264 -0.0213 0.8122 0.1043
-3.750 -0.2645 0.00848 0.00250 -0.0203 0.7874 0.1153
-3.500 -0.2404 0.00842 0.00237 -0.0194 0.7627 0.1260
-3.250 -0.2163 0.00835 0.00225 -0.0185 0.7370 0.1381
-3.000 -0.1923 0.00828 0.00214 -0.0176 0.7130 0.1532
-2.750 -0.1688 0.00815 0.00202 -0.0166 0.6899 0.1767
-2.500 -0.1479 0.00782 0.00184 -0.0152 0.6693 0.2368
-2.250 -0.1319 0.00716 0.00166 -0.0129 0.6515 0.3851
-2.000 -0.1102 0.00692 0.00158 -0.0116 0.6343 0.4482
-1.750 -0.0878 0.00673 0.00152 -0.0104 0.6181 0.5033
-1.500 -0.0650 0.00657 0.00147 -0.0092 0.6033 0.5519
-1.250 -0.0418 0.00644 0.00143 -0.0081 0.5893 0.5934
-1.000 -0.0189 0.00631 0.00140 -0.0070 0.5760 0.6373
-0.750 0.0043 0.00622 0.00138 -0.0058 0.5637 0.6768
-0.500 0.0277 0.00616 0.00138 -0.0047 0.5512 0.7130
-0.250 0.0516 0.00612 0.00139 -0.0037 0.5385 0.7441
0.000 0.0764 0.00610 0.00140 -0.0029 0.5264 0.7690
0.250 0.1013 0.00610 0.00142 -0.0021 0.5145 0.7918
0.500 0.1266 0.00612 0.00144 -0.0013 0.5025 0.8114
0.750 0.1522 0.00615 0.00146 -0.0007 0.4899 0.8283
1.000 0.1781 0.00617 0.00149 -0.0001 0.4773 0.8456
1.250 0.2041 0.00620 0.00152 0.0004 0.4649 0.8629
1.500 0.2305 0.00625 0.00157 0.0009 0.4526 0.8805
1.750 0.2577 0.00631 0.00162 0.0011 0.4400 0.8984
2.000 0.2854 0.00636 0.00166 0.0012 0.4275 0.9123
2.250 0.3167 0.00643 0.00171 0.0005 0.4152 0.9222
2.500 0.3488 0.00652 0.00176 -0.0004 0.4037 0.9320
2.750 0.3816 0.00662 0.00182 -0.0016 0.3915 0.9421
3.000 0.4232 0.00674 0.00190 -0.0048 0.3784 0.9475
3.250 0.4642 0.00686 0.00199 -0.0078 0.3672 0.9532
3.500 0.5061 0.00701 0.00209 -0.0111 0.3548 0.9573
3.750 0.5487 0.00718 0.00221 -0.0146 0.3424 0.9602
4.000 0.5893 0.00736 0.00235 -0.0175 0.3311 0.9638
4.250 0.6263 0.00753 0.00249 -0.0196 0.3209 0.9683
4.500 0.6632 0.00773 0.00265 -0.0217 0.3101 0.9708
5.000 0.7307 0.00813 0.00296 -0.0244 0.2882 0.9775
5.250 0.7637 0.00833 0.00313 -0.0257 0.2781 0.9815
5.500 0.7947 0.00857 0.00332 -0.0265 0.2674 0.9868
5.750 0.8269 0.00877 0.00351 -0.0276 0.2575 0.9925
6.000 0.8604 0.00902 0.00371 -0.0290 0.2464 0.9954
6.250 0.8958 0.00924 0.00389 -0.0309 0.2337 0.9971
6.500 0.9303 0.00950 0.00407 -0.0326 0.2176 0.9987
6.750 0.9640 0.00978 0.00428 -0.0341 0.2014 0.9999
7.000 0.9851 0.01001 0.00445 -0.0330 0.1905 1.0000
7.250 1.0050 0.01020 0.00462 -0.0315 0.1819 1.0000
7.500 1.0255 0.01043 0.00482 -0.0302 0.1727 1.0000
8.000 1.0684 0.01094 0.00527 -0.0279 0.1556 1.0000
8.250 1.0899 0.01124 0.00553 -0.0268 0.1470 1.0000
8.500 1.1120 0.01151 0.00578 -0.0258 0.1394 1.0000
8.750 1.1341 0.01181 0.00606 -0.0248 0.1324 1.0000
9.000 1.1560 0.01212 0.00634 -0.0238 0.1246 1.0000
9.250 1.1779 0.01245 0.00665 -0.0229 0.1161 1.0000
9.500 1.1982 0.01289 0.00703 -0.0217 0.1031 1.0000
9.750 1.2144 0.01364 0.00760 -0.0199 0.0778 1.0000
10.000 1.2148 0.01552 0.00908 -0.0157 0.0257 1.0000
10.250 1.2309 0.01624 0.00979 -0.0138 0.0201 1.0000
10.500 1.2485 0.01682 0.01039 -0.0123 0.0179 1.0000
10.750 1.2646 0.01749 0.01110 -0.0105 0.0163 1.0000
11.000 1.2824 0.01800 0.01166 -0.0090 0.0155 1.0000
11.250 1.2987 0.01860 0.01230 -0.0073 0.0147 1.0000
11.500 1.3132 0.01929 0.01303 -0.0054 0.0140 1.0000
11.750 1.3215 0.02014 0.01394 -0.0024 0.0133 1.0000
12.000 1.3274 0.02090 0.01477 0.0010 0.0129 1.0000
12.250 1.3373 0.02155 0.01548 0.0035 0.0126 1.0000
12.500 1.3460 0.02234 0.01634 0.0060 0.0123 1.0000
12.750 1.3540 0.02326 0.01732 0.0083 0.0119 1.0000
13.000 1.3616 0.02430 0.01842 0.0103 0.0116 1.0000
13.250 1.3680 0.02551 0.01969 0.0122 0.0113 1.0000
13.500 1.3729 0.02694 0.02119 0.0139 0.0111 1.0000
13.750 1.3755 0.02867 0.02300 0.0154 0.0108 1.0000
14.000 1.3736 0.03096 0.02539 0.0166 0.0106 1.0000
14.250 1.3681 0.03386 0.02841 0.0174 0.0104 1.0000
14.500 1.3584 0.03752 0.03220 0.0175 0.0102 1.0000
14.750 1.3581 0.04039 0.03517 0.0173 0.0101 1.0000
15.000 1.3576 0.04342 0.03829 0.0168 0.0100 1.0000
15.250 1.3534 0.04700 0.04198 0.0160 0.0100 1.0000
15.500 1.3476 0.05087 0.04595 0.0150 0.0099 1.0000
15.750 1.3381 0.05532 0.05051 0.0138 0.0098 1.0000
16.000 1.3280 0.05987 0.05517 0.0125 0.0097 1.0000
16.250 1.3164 0.06477 0.06018 0.0110 0.0097 1.0000
16.500 1.3027 0.07008 0.06561 0.0092 0.0096 1.0000
16.750 1.2896 0.07540 0.07103 0.0074 0.0095 1.0000
17.000 1.2742 0.08120 0.07694 0.0053 0.0095 1.0000
17.250 1.2598 0.08690 0.08274 0.0032 0.0095 1.0000
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Polar data table (+)
Polar graphs
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