GIII BL369 AIRFOIL (giiik-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GIII BL369 AIRFOIL (giiik-il) Reynolds number: 200,000 Max Cl/Cd: 58.03 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiik-il-200000.txt Download as CSV file: xf-giiik-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL369 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5550 0.08786 0.08427 -0.0080 1.0000 0.0425
-8.250 -0.5556 0.08344 0.07989 -0.0118 1.0000 0.0434
-8.000 -0.5577 0.07868 0.07512 -0.0165 1.0000 0.0442
-7.750 -0.5558 0.07401 0.07039 -0.0204 1.0000 0.0456
-7.500 -0.5535 0.06944 0.06552 -0.0260 1.0000 0.0482
-7.250 -0.5500 0.06697 0.06264 -0.0270 1.0000 0.0488
-7.000 -0.5459 0.05980 0.05550 -0.0276 1.0000 0.0497
-6.750 -0.5340 0.05610 0.05187 -0.0273 1.0000 0.0506
-6.500 -0.5218 0.05322 0.04897 -0.0268 1.0000 0.0517
-6.250 -0.5093 0.05049 0.04617 -0.0262 1.0000 0.0533
-6.000 -0.4965 0.04779 0.04334 -0.0254 1.0000 0.0558
-5.750 -0.4799 0.04885 0.04365 -0.0228 1.0000 0.0609
-5.500 -0.4743 0.04197 0.03685 -0.0222 1.0000 0.0626
-5.250 -0.4610 0.03940 0.03433 -0.0209 1.0000 0.0643
-5.000 -0.4477 0.03744 0.03231 -0.0193 1.0000 0.0670
-4.750 -0.4297 0.03992 0.03411 -0.0158 1.0000 0.0747
-4.500 -0.4220 0.03343 0.02783 -0.0153 1.0000 0.0779
-4.250 -0.4074 0.03187 0.02628 -0.0137 1.0000 0.0828
-4.000 -0.3932 0.03020 0.02432 -0.0119 1.0000 0.0927
-3.750 -0.3768 0.02867 0.02278 -0.0105 1.0000 0.0982
-3.500 -0.3606 0.02708 0.02104 -0.0092 1.0000 0.1098
-3.250 -0.3404 0.02568 0.01952 -0.0087 0.9994 0.1248
-3.000 -0.2888 0.02222 0.01477 -0.0077 0.9964 0.0615
-2.750 -0.2501 0.01993 0.01234 -0.0098 0.9931 0.0596
-2.500 -0.2116 0.01797 0.01021 -0.0116 0.9890 0.0578
-2.250 -0.1707 0.01672 0.00883 -0.0139 0.9851 0.0582
-2.000 -0.1314 0.01627 0.00825 -0.0160 0.9789 0.0609
-1.750 -0.0929 0.01471 0.00675 -0.0181 0.9744 0.0630
-1.500 -0.0531 0.01390 0.00605 -0.0207 0.9691 0.0677
-1.250 -0.0150 0.01332 0.00550 -0.0228 0.9618 0.0722
-1.000 0.0279 0.01263 0.00485 -0.0259 0.9573 0.0779
-0.750 0.0622 0.01223 0.00447 -0.0271 0.9475 0.0889
-0.500 0.0908 0.01022 0.00398 -0.0281 0.9395 0.4909
-0.250 0.1150 0.00932 0.00459 -0.0235 0.9332 0.9467
0.000 0.2033 0.00935 0.00450 -0.0345 0.9353 0.9897
0.250 0.2579 0.00915 0.00422 -0.0397 0.9251 1.0000
0.500 0.2810 0.00904 0.00406 -0.0385 0.9048 1.0000
0.750 0.3027 0.00895 0.00391 -0.0370 0.8846 1.0000
1.000 0.3240 0.00886 0.00374 -0.0352 0.8642 1.0000
1.250 0.3451 0.00882 0.00363 -0.0336 0.8409 1.0000
1.500 0.3669 0.00879 0.00351 -0.0320 0.8188 1.0000
1.750 0.3894 0.00879 0.00345 -0.0307 0.7954 1.0000
2.000 0.4121 0.00882 0.00337 -0.0293 0.7714 1.0000
2.250 0.4346 0.00887 0.00331 -0.0279 0.7418 1.0000
2.500 0.4572 0.00895 0.00327 -0.0265 0.7100 1.0000
2.750 0.4804 0.00907 0.00328 -0.0254 0.6788 1.0000
3.000 0.5036 0.00921 0.00331 -0.0242 0.6462 1.0000
3.250 0.5267 0.00938 0.00337 -0.0231 0.6111 1.0000
3.500 0.5494 0.00961 0.00345 -0.0219 0.5741 1.0000
3.750 0.5719 0.00989 0.00356 -0.0208 0.5338 1.0000
4.000 0.5939 0.01024 0.00371 -0.0196 0.4905 1.0000
4.250 0.6157 0.01061 0.00392 -0.0184 0.4431 1.0000
4.500 0.6372 0.01104 0.00413 -0.0172 0.3833 1.0000
4.750 0.6572 0.01168 0.00440 -0.0160 0.3062 1.0000
5.000 0.6765 0.01252 0.00483 -0.0147 0.2287 1.0000
5.250 0.6962 0.01343 0.00540 -0.0136 0.1702 1.0000
5.500 0.7168 0.01429 0.00602 -0.0126 0.1362 1.0000
5.750 0.7381 0.01509 0.00669 -0.0116 0.1158 1.0000
6.000 0.7597 0.01589 0.00742 -0.0106 0.1021 1.0000
6.250 0.7807 0.01682 0.00827 -0.0096 0.0926 1.0000
6.500 0.8036 0.01755 0.00906 -0.0088 0.0859 1.0000
6.750 0.8250 0.01856 0.00998 -0.0079 0.0799 1.0000
7.000 0.8481 0.01946 0.01098 -0.0071 0.0757 1.0000
7.250 0.8713 0.02030 0.01186 -0.0064 0.0716 1.0000
7.500 0.8937 0.02147 0.01298 -0.0058 0.0677 1.0000
7.750 0.9168 0.02272 0.01435 -0.0051 0.0648 1.0000
8.000 0.9401 0.02365 0.01544 -0.0044 0.0616 1.0000
8.250 0.9627 0.02457 0.01640 -0.0038 0.0584 1.0000
8.500 0.9845 0.02688 0.01873 -0.0033 0.0557 1.0000
8.750 1.0057 0.02799 0.02013 -0.0023 0.0537 1.0000
9.000 1.0264 0.02925 0.02164 -0.0014 0.0511 1.0000
9.250 1.0466 0.03060 0.02313 -0.0006 0.0489 1.0000
9.500 1.0661 0.03228 0.02490 0.0001 0.0472 1.0000
9.750 1.0796 0.03631 0.02918 0.0011 0.0456 1.0000
10.000 1.0918 0.03805 0.03137 0.0029 0.0445 1.0000
10.250 1.1005 0.04064 0.03442 0.0047 0.0431 1.0000
10.500 1.1053 0.04383 0.03800 0.0065 0.0421 1.0000
10.750 1.1036 0.04763 0.04221 0.0085 0.0417 1.0000
11.000 1.0941 0.05193 0.04690 0.0106 0.0415 1.0000
11.250 1.0749 0.05644 0.05175 0.0130 0.0417 1.0000
11.500 1.0489 0.06115 0.05673 0.0144 0.0421 1.0000
11.750 1.0199 0.06678 0.06259 0.0134 0.0426 1.0000
12.000 0.9889 0.07385 0.06986 0.0096 0.0432 1.0000
12.250 0.9560 0.08297 0.07912 0.0030 0.0439 1.0000
12.500 0.9246 0.09374 0.08996 -0.0047 0.0448 1.0000
12.750 0.9104 0.10130 0.09752 -0.0077 0.0456 1.0000
13.000 0.6607 0.13213 0.12852 -0.0106 0.0787 1.0000
13.250 0.6320 0.13794 0.13430 -0.0160 0.0779 1.0000
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Polar data table (+)
Polar graphs
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