GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 50,000 Max Cl/Cd: 32.43 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiig-il-50000-n5.txt Download as CSV file: xf-giiig-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL167 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5635 0.10445 0.09771 -0.0054 1.0000 0.1026
-8.750 -0.5635 0.10021 0.09352 -0.0080 1.0000 0.1024
-8.500 -0.5735 0.09057 0.08383 -0.0203 1.0000 0.0537
-8.250 -0.5676 0.08635 0.07965 -0.0197 1.0000 0.0514
-8.000 -0.5672 0.08188 0.07517 -0.0216 1.0000 0.0497
-7.750 -0.5670 0.07727 0.07053 -0.0236 1.0000 0.0481
-7.500 -0.5660 0.07255 0.06572 -0.0253 1.0000 0.0465
-7.250 -0.5638 0.06768 0.06070 -0.0267 1.0000 0.0450
-7.000 -0.5600 0.06258 0.05531 -0.0277 1.0000 0.0433
-6.750 -0.5530 0.05798 0.05031 -0.0277 1.0000 0.0422
-6.500 -0.5421 0.05507 0.04739 -0.0271 1.0000 0.0445
-6.250 -0.5306 0.05195 0.04406 -0.0264 1.0000 0.0469
-6.000 -0.5183 0.04851 0.04029 -0.0255 1.0000 0.0485
-5.750 -0.5048 0.04498 0.03637 -0.0244 1.0000 0.0488
-5.500 -0.4897 0.04160 0.03256 -0.0230 1.0000 0.0490
-5.250 -0.4731 0.03849 0.02899 -0.0214 1.0000 0.0495
-5.000 -0.4548 0.03560 0.02556 -0.0199 1.0000 0.0505
-4.750 -0.4346 0.03309 0.02248 -0.0183 1.0000 0.0531
-4.500 -0.4150 0.03102 0.02017 -0.0171 1.0000 0.0579
-4.250 -0.3932 0.02917 0.01806 -0.0159 1.0000 0.0620
-4.000 -0.3691 0.02725 0.01576 -0.0147 1.0000 0.0656
-3.750 -0.3450 0.02564 0.01399 -0.0136 1.0000 0.0717
-3.500 -0.3214 0.02452 0.01269 -0.0125 1.0000 0.0831
-3.250 -0.2976 0.02330 0.01133 -0.0115 1.0000 0.0923
-3.000 -0.2762 0.02239 0.01031 -0.0103 1.0000 0.1093
-2.750 -0.2573 0.02144 0.00938 -0.0089 1.0000 0.1267
-2.500 -0.2392 0.02055 0.00853 -0.0075 1.0000 0.1529
-2.000 -0.0576 0.01731 0.00755 -0.0251 1.0000 1.0000
-1.750 -0.0525 0.01724 0.00736 -0.0220 1.0000 1.0000
-1.500 -0.0502 0.01721 0.00723 -0.0183 1.0000 1.0000
-1.250 -0.0493 0.01722 0.00712 -0.0145 1.0000 1.0000
-1.000 -0.0475 0.01726 0.00700 -0.0108 1.0000 1.0000
-0.750 -0.0433 0.01733 0.00694 -0.0076 1.0000 1.0000
-0.500 -0.0341 0.01744 0.00690 -0.0052 0.9994 1.0000
-0.250 0.0023 0.01764 0.00694 -0.0080 0.9902 1.0000
0.000 0.0381 0.01787 0.00700 -0.0105 0.9811 1.0000
0.250 0.0737 0.01811 0.00713 -0.0130 0.9720 1.0000
0.500 0.1103 0.01836 0.00731 -0.0155 0.9634 1.0000
0.750 0.1454 0.01861 0.00752 -0.0178 0.9540 1.0000
1.000 0.1794 0.01886 0.00776 -0.0197 0.9441 1.0000
1.250 0.2167 0.01912 0.00803 -0.0222 0.9348 1.0000
1.500 0.2592 0.01933 0.00830 -0.0256 0.9247 1.0000
1.750 0.2975 0.01949 0.00856 -0.0278 0.9116 1.0000
2.000 0.3339 0.01964 0.00880 -0.0296 0.8979 1.0000
2.250 0.3676 0.01979 0.00907 -0.0308 0.8842 1.0000
2.500 0.3997 0.01994 0.00940 -0.0315 0.8704 1.0000
2.750 0.4306 0.02007 0.00970 -0.0319 0.8560 1.0000
3.000 0.4604 0.02019 0.00999 -0.0320 0.8410 1.0000
3.250 0.4861 0.02036 0.01034 -0.0313 0.8240 1.0000
3.500 0.5126 0.02048 0.01074 -0.0305 0.8062 1.0000
3.750 0.5402 0.02053 0.01103 -0.0297 0.7878 1.0000
4.000 0.5651 0.02057 0.01132 -0.0283 0.7663 1.0000
4.250 0.5886 0.02029 0.01125 -0.0258 0.7330 1.0000
4.500 0.6073 0.01965 0.01065 -0.0213 0.6723 1.0000
4.750 0.6240 0.01936 0.01034 -0.0171 0.5857 1.0000
5.000 0.6388 0.01970 0.01007 -0.0129 0.4385 1.0000
5.250 0.6464 0.02152 0.01072 -0.0096 0.2543 1.0000
5.500 0.6564 0.02384 0.01214 -0.0076 0.1401 1.0000
5.750 0.6714 0.02570 0.01363 -0.0062 0.1031 1.0000
6.000 0.6895 0.02729 0.01527 -0.0047 0.0881 1.0000
6.250 0.7094 0.02889 0.01694 -0.0033 0.0778 1.0000
6.500 0.7313 0.03037 0.01867 -0.0023 0.0669 1.0000
6.750 0.7559 0.03231 0.02072 -0.0014 0.0613 1.0000
7.000 0.7830 0.03452 0.02325 -0.0006 0.0572 1.0000
7.250 0.8063 0.03682 0.02573 0.0002 0.0527 1.0000
7.500 0.8267 0.03944 0.02872 0.0011 0.0480 1.0000
7.750 0.8460 0.04251 0.03232 0.0024 0.0456 1.0000
8.000 0.8616 0.04593 0.03625 0.0038 0.0442 1.0000
8.250 0.8734 0.04950 0.04030 0.0052 0.0430 1.0000
8.500 0.8831 0.05270 0.04381 0.0064 0.0410 1.0000
8.750 0.8909 0.05620 0.04749 0.0072 0.0387 1.0000
9.000 0.8897 0.06014 0.05189 0.0088 0.0377 1.0000
9.250 0.8849 0.06418 0.05638 0.0102 0.0372 1.0000
9.500 0.8767 0.06836 0.06087 0.0112 0.0370 1.0000
9.750 0.8650 0.07250 0.06524 0.0120 0.0371 1.0000
10.000 0.8499 0.07666 0.06956 0.0122 0.0372 1.0000
10.250 0.8342 0.08131 0.07433 0.0111 0.0374 1.0000
10.500 0.8189 0.08658 0.07968 0.0086 0.0376 1.0000
10.750 0.8051 0.09244 0.08559 0.0052 0.0378 1.0000
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