Falcon (falcon-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Falcon (falcon-il) Reynolds number: 50,000 Max Cl/Cd: 22.21 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-falcon-il-50000.txt Download as CSV file: xf-falcon-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3228 0.11066 0.10385 -0.0089 1.0000 0.3441
-9.750 -0.3319 0.10849 0.10175 -0.0082 1.0000 0.3582
-9.500 -0.3315 0.10572 0.09900 -0.0074 1.0000 0.3734
-9.250 -0.3050 0.10078 0.09403 -0.0073 1.0000 0.3850
-9.000 -0.3023 0.09722 0.09051 -0.0069 1.0000 0.3954
-8.750 -0.3145 0.09450 0.08786 -0.0060 1.0000 0.4073
-8.500 -0.6387 0.07525 0.06834 -0.0271 1.0000 0.1832
-8.250 -0.6490 0.06867 0.06160 -0.0269 1.0000 0.1687
-8.000 -0.6555 0.06396 0.05669 -0.0255 1.0000 0.1617
-7.750 -0.6636 0.05933 0.05184 -0.0233 1.0000 0.1568
-7.500 -0.6847 0.05513 0.04683 -0.0191 1.0000 0.1495
-7.250 -0.6781 0.05142 0.04289 -0.0168 1.0000 0.1485
-7.000 -0.6732 0.04817 0.03928 -0.0140 1.0000 0.1485
-6.750 -0.6694 0.04556 0.03613 -0.0106 1.0000 0.1500
-6.500 -0.6530 0.04250 0.03319 -0.0093 1.0000 0.1549
-6.250 -0.6406 0.04006 0.03047 -0.0069 1.0000 0.1582
-6.000 -0.6283 0.03786 0.02787 -0.0043 1.0000 0.1629
-5.750 -0.6136 0.03564 0.02539 -0.0021 1.0000 0.1696
-5.500 -0.5955 0.03372 0.02332 -0.0004 1.0000 0.1776
-5.250 -0.5771 0.03182 0.02126 0.0013 1.0000 0.1881
-5.000 -0.5570 0.03012 0.01937 0.0028 1.0000 0.2010
-4.750 -0.5345 0.02845 0.01776 0.0039 1.0000 0.2184
-4.500 -0.5107 0.02692 0.01638 0.0047 1.0000 0.2407
-4.250 -0.4870 0.02555 0.01524 0.0056 1.0000 0.2693
-4.000 -0.4659 0.02440 0.01433 0.0068 1.0000 0.3090
-3.750 -0.4484 0.02315 0.01369 0.0085 1.0000 0.3726
-3.500 -0.4430 0.02151 0.01355 0.0135 1.0000 0.5488
-3.250 -0.4309 0.02200 0.01498 0.0221 1.0000 0.7805
-3.000 -0.3616 0.02428 0.01690 0.0214 1.0000 0.8835
-2.750 -0.1167 0.02669 0.01810 -0.0112 1.0000 0.9613
-2.500 0.0169 0.02571 0.01662 -0.0319 1.0000 1.0000
-2.250 0.0090 0.02548 0.01643 -0.0287 1.0000 1.0000
-2.000 -0.0099 0.02552 0.01652 -0.0240 1.0000 1.0000
-1.750 -0.0372 0.02576 0.01679 -0.0184 1.0000 1.0000
-1.500 -0.0653 0.02605 0.01709 -0.0129 1.0000 1.0000
-1.250 -0.0894 0.02632 0.01734 -0.0079 1.0000 1.0000
-1.000 -0.0282 0.02662 0.01746 -0.0169 0.9826 1.0000
-0.750 0.0439 0.02676 0.01740 -0.0271 0.9613 1.0000
-0.500 0.1195 0.02675 0.01725 -0.0374 0.9417 1.0000
-0.250 0.1849 0.02668 0.01707 -0.0454 0.9201 1.0000
0.000 0.2530 0.02642 0.01673 -0.0534 0.8998 1.0000
0.250 0.3118 0.02610 0.01634 -0.0591 0.8796 1.0000
0.500 0.3432 0.02617 0.01636 -0.0601 0.8555 1.0000
0.750 0.3797 0.02606 0.01620 -0.0615 0.8344 1.0000
1.000 0.4129 0.02595 0.01602 -0.0619 0.8149 1.0000
1.250 0.4327 0.02621 0.01624 -0.0605 0.7937 1.0000
1.500 0.4541 0.02642 0.01641 -0.0591 0.7740 1.0000
1.750 0.4758 0.02663 0.01657 -0.0577 0.7554 1.0000
2.000 0.4969 0.02687 0.01677 -0.0561 0.7377 1.0000
2.250 0.5172 0.02716 0.01701 -0.0544 0.7204 1.0000
2.500 0.5370 0.02750 0.01732 -0.0526 0.7035 1.0000
2.750 0.5563 0.02790 0.01767 -0.0508 0.6869 1.0000
3.000 0.5752 0.02834 0.01809 -0.0489 0.6705 1.0000
3.250 0.5936 0.02884 0.01857 -0.0469 0.6544 1.0000
3.500 0.6119 0.02938 0.01908 -0.0450 0.6384 1.0000
3.750 0.6299 0.02996 0.01966 -0.0431 0.6226 1.0000
4.000 0.6477 0.03059 0.02029 -0.0411 0.6070 1.0000
4.250 0.6653 0.03127 0.02097 -0.0392 0.5915 1.0000
4.500 0.6830 0.03197 0.02168 -0.0372 0.5761 1.0000
4.750 0.7007 0.03271 0.02242 -0.0353 0.5611 1.0000
5.000 0.7189 0.03342 0.02316 -0.0335 0.5461 1.0000
5.250 0.7377 0.03414 0.02390 -0.0317 0.5316 1.0000
5.500 0.7579 0.03477 0.02452 -0.0299 0.5173 1.0000
5.750 0.7806 0.03525 0.02500 -0.0284 0.5034 1.0000
6.000 0.7998 0.03601 0.02579 -0.0267 0.4893 1.0000
6.250 0.8127 0.03723 0.02710 -0.0246 0.4748 1.0000
6.500 0.8234 0.03869 0.02866 -0.0224 0.4611 1.0000
6.750 0.8358 0.04010 0.03015 -0.0204 0.4481 1.0000
7.000 0.8545 0.04107 0.03118 -0.0187 0.4359 1.0000
7.250 0.8837 0.04132 0.03139 -0.0178 0.4245 1.0000
7.500 0.8750 0.04449 0.03480 -0.0147 0.4129 1.0000
7.750 0.8815 0.04662 0.03703 -0.0126 0.4026 1.0000
8.000 0.9209 0.04614 0.03653 -0.0123 0.3924 1.0000
8.250 0.8716 0.05295 0.04361 -0.0080 0.3841 1.0000
8.500 0.9207 0.05188 0.04255 -0.0080 0.3758 1.0000
8.750 0.7909 0.06660 0.05726 -0.0041 0.3728 1.0000
9.000 0.7061 0.08019 0.07066 -0.0080 0.3721 1.0000
9.250 0.6790 0.08710 0.07753 -0.0098 0.3708 1.0000
9.500 0.6634 0.09285 0.08325 -0.0112 0.3707 1.0000
9.750 0.6579 0.09805 0.08848 -0.0126 0.3733 1.0000
10.000 0.5774 0.11602 0.10641 -0.0255 0.4889 1.0000
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Polar data table (+)
Polar graphs
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