Falcon (falcon-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 100,000 Max Cl/Cd: 44.33 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-falcon-il-100000-n5.txt Download as CSV file: xf-falcon-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6225 0.09077 0.08542 -0.0293 1.0000 0.0366
-11.500 -0.6777 0.07434 0.06887 -0.0411 1.0000 0.0354
-11.250 -0.7220 0.06518 0.05949 -0.0463 1.0000 0.0348
-11.000 -0.7546 0.05954 0.05362 -0.0467 1.0000 0.0346
-10.750 -0.7798 0.05560 0.04945 -0.0445 1.0000 0.0348
-10.500 -0.8005 0.05238 0.04600 -0.0407 1.0000 0.0351
-10.250 -0.8141 0.04910 0.04240 -0.0372 1.0000 0.0357
-10.000 -0.8230 0.04585 0.03878 -0.0337 1.0000 0.0363
-9.750 -0.8268 0.04272 0.03523 -0.0303 1.0000 0.0370
-9.500 -0.8255 0.03984 0.03189 -0.0272 1.0000 0.0377
-9.250 -0.8171 0.03761 0.02942 -0.0248 1.0000 0.0384
-9.000 -0.8040 0.03624 0.02800 -0.0230 1.0000 0.0394
-8.750 -0.7905 0.03503 0.02669 -0.0211 1.0000 0.0408
-8.500 -0.7768 0.03360 0.02506 -0.0191 1.0000 0.0426
-8.250 -0.7621 0.03195 0.02312 -0.0171 1.0000 0.0443
-8.000 -0.7457 0.03032 0.02119 -0.0152 1.0000 0.0458
-7.750 -0.7289 0.02906 0.01995 -0.0136 1.0000 0.0473
-7.500 -0.7121 0.02815 0.01902 -0.0119 1.0000 0.0493
-7.250 -0.6949 0.02721 0.01797 -0.0102 1.0000 0.0521
-7.000 -0.6768 0.02619 0.01673 -0.0084 1.0000 0.0549
-6.750 -0.6607 0.02526 0.01587 -0.0066 1.0000 0.0573
-6.500 -0.6444 0.02452 0.01512 -0.0046 1.0000 0.0603
-6.250 -0.6276 0.02382 0.01430 -0.0027 1.0000 0.0646
-6.000 -0.6126 0.02314 0.01366 -0.0006 1.0000 0.0685
-5.750 -0.5971 0.02258 0.01308 0.0015 1.0000 0.0733
-5.500 -0.5775 0.02195 0.01244 0.0027 0.9988 0.0794
-5.250 -0.5408 0.02124 0.01169 0.0005 0.9902 0.0893
-5.000 -0.5062 0.02054 0.01103 -0.0014 0.9799 0.1005
-4.750 -0.4704 0.01988 0.01039 -0.0033 0.9706 0.1137
-4.500 -0.4336 0.01925 0.00977 -0.0054 0.9619 0.1292
-4.250 -0.3940 0.01861 0.00914 -0.0081 0.9546 0.1481
-4.000 -0.3577 0.01796 0.00855 -0.0100 0.9445 0.1693
-3.500 -0.2929 0.01617 0.00742 -0.0127 0.9210 0.2794
-3.250 -0.2680 0.01516 0.00717 -0.0122 0.9065 0.4497
-3.000 -0.2405 0.01465 0.00700 -0.0118 0.8911 0.5453
-2.750 -0.2119 0.01432 0.00692 -0.0113 0.8748 0.6201
-2.500 -0.1814 0.01413 0.00688 -0.0111 0.8578 0.6793
-2.250 -0.1498 0.01405 0.00683 -0.0110 0.8400 0.7251
-2.000 -0.1184 0.01401 0.00677 -0.0110 0.8213 0.7632
-1.750 -0.0857 0.01402 0.00671 -0.0111 0.8024 0.7945
-1.500 -0.0511 0.01407 0.00667 -0.0117 0.7832 0.8219
-1.250 -0.0178 0.01416 0.00665 -0.0120 0.7632 0.8483
-1.000 0.0205 0.01434 0.00671 -0.0133 0.7428 0.8717
-0.750 0.0578 0.01449 0.00672 -0.0145 0.7227 0.8900
-0.500 0.0940 0.01459 0.00665 -0.0159 0.7031 0.9018
-0.250 0.1275 0.01468 0.00657 -0.0168 0.6845 0.9135
0.000 0.1656 0.01480 0.00654 -0.0187 0.6655 0.9223
0.250 0.2021 0.01491 0.00650 -0.0204 0.6474 0.9314
0.500 0.2383 0.01503 0.00649 -0.0220 0.6300 0.9407
0.750 0.2779 0.01518 0.00650 -0.0243 0.6127 0.9477
1.000 0.3136 0.01531 0.00652 -0.0260 0.5965 0.9567
1.250 0.3536 0.01545 0.00654 -0.0285 0.5800 0.9634
1.500 0.3911 0.01558 0.00658 -0.0306 0.5644 0.9711
1.750 0.4280 0.01572 0.00662 -0.0326 0.5489 0.9790
2.000 0.4648 0.01586 0.00668 -0.0347 0.5338 0.9866
2.250 0.5012 0.01601 0.00674 -0.0368 0.5188 0.9943
2.500 0.5384 0.01613 0.00678 -0.0390 0.5039 1.0000
2.750 0.5593 0.01621 0.00683 -0.0380 0.4905 1.0000
3.000 0.5801 0.01631 0.00689 -0.0369 0.4774 1.0000
3.250 0.6007 0.01643 0.00697 -0.0357 0.4647 1.0000
3.500 0.6211 0.01658 0.00705 -0.0344 0.4526 1.0000
3.750 0.6414 0.01674 0.00717 -0.0331 0.4406 1.0000
4.000 0.6617 0.01690 0.00732 -0.0318 0.4279 1.0000
4.250 0.6820 0.01710 0.00749 -0.0305 0.4159 1.0000
4.500 0.7023 0.01731 0.00768 -0.0292 0.4044 1.0000
4.750 0.7225 0.01754 0.00787 -0.0279 0.3931 1.0000
5.000 0.7430 0.01778 0.00812 -0.0266 0.3813 1.0000
5.250 0.7634 0.01805 0.00837 -0.0253 0.3700 1.0000
5.500 0.7836 0.01834 0.00863 -0.0240 0.3594 1.0000
5.750 0.8041 0.01863 0.00895 -0.0227 0.3479 1.0000
6.000 0.8246 0.01895 0.00929 -0.0214 0.3369 1.0000
6.250 0.8448 0.01930 0.00962 -0.0201 0.3266 1.0000
6.500 0.8650 0.01966 0.01000 -0.0188 0.3158 1.0000
6.750 0.8852 0.02003 0.01041 -0.0176 0.3050 1.0000
7.000 0.9049 0.02044 0.01081 -0.0162 0.2951 1.0000
7.250 0.9247 0.02086 0.01128 -0.0149 0.2849 1.0000
7.500 0.9445 0.02131 0.01178 -0.0136 0.2755 1.0000
7.750 0.9635 0.02179 0.01224 -0.0121 0.2669 1.0000
8.000 0.9829 0.02228 0.01283 -0.0108 0.2573 1.0000
8.250 1.0015 0.02281 0.01337 -0.0094 0.2492 1.0000
8.500 1.0203 0.02335 0.01400 -0.0080 0.2407 1.0000
8.750 1.0386 0.02394 0.01460 -0.0065 0.2340 1.0000
9.000 1.0571 0.02454 0.01532 -0.0052 0.2269 1.0000
9.250 1.0748 0.02518 0.01596 -0.0037 0.2212 1.0000
9.500 1.0925 0.02583 0.01677 -0.0022 0.2141 1.0000
9.750 1.1085 0.02646 0.01741 -0.0006 0.2073 1.0000
10.000 1.1232 0.02711 0.01820 0.0013 0.1986 1.0000
10.250 1.1356 0.02775 0.01883 0.0033 0.1902 1.0000
10.500 1.1472 0.02842 0.01966 0.0054 0.1807 1.0000
10.750 1.1580 0.02917 0.02047 0.0076 0.1728 1.0000
11.000 1.1663 0.02995 0.02133 0.0101 0.1645 1.0000
11.250 1.1730 0.03079 0.02229 0.0128 0.1567 1.0000
11.500 1.1762 0.03176 0.02329 0.0156 0.1490 1.0000
11.750 1.1814 0.03282 0.02451 0.0179 0.1397 1.0000
12.000 1.1838 0.03414 0.02593 0.0200 0.1304 1.0000
12.250 1.1840 0.03577 0.02761 0.0219 0.1203 1.0000
12.500 1.1841 0.03764 0.02958 0.0233 0.1084 1.0000
12.750 1.1820 0.03992 0.03195 0.0243 0.0943 1.0000
13.000 1.1757 0.04283 0.03489 0.0249 0.0774 1.0000
13.250 1.1629 0.04668 0.03871 0.0248 0.0630 1.0000
13.500 1.1480 0.05115 0.04319 0.0241 0.0543 1.0000
13.750 1.1325 0.05604 0.04813 0.0229 0.0496 1.0000
14.000 1.1153 0.06142 0.05360 0.0212 0.0465 1.0000
14.250 1.0971 0.06720 0.05947 0.0192 0.0447 1.0000
14.500 1.0799 0.07302 0.06543 0.0170 0.0433 1.0000
14.750 1.0621 0.07913 0.07167 0.0147 0.0420 1.0000
15.000 1.0445 0.08539 0.07805 0.0123 0.0410 1.0000
15.250 1.0273 0.09176 0.08454 0.0097 0.0400 1.0000
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