GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 50,000 Max Cl/Cd: 29.58 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiib-il-50000-n5.txt Download as CSV file: xf-giiib-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6297 0.09473 0.08788 -0.0160 1.0000 0.0467
-10.000 -0.6382 0.08825 0.08142 -0.0203 1.0000 0.0463
-9.750 -0.6509 0.08234 0.07550 -0.0238 1.0000 0.0459
-9.500 -0.6663 0.07717 0.07029 -0.0258 1.0000 0.0455
-9.250 -0.6824 0.07269 0.06572 -0.0259 1.0000 0.0452
-9.000 -0.6958 0.06831 0.06120 -0.0254 1.0000 0.0450
-8.750 -0.7053 0.06397 0.05665 -0.0244 1.0000 0.0449
-8.500 -0.7113 0.05972 0.05210 -0.0230 1.0000 0.0450
-8.250 -0.7138 0.05558 0.04761 -0.0213 1.0000 0.0452
-8.000 -0.7133 0.05163 0.04321 -0.0192 1.0000 0.0461
-7.750 -0.7100 0.04795 0.03892 -0.0168 1.0000 0.0476
-7.500 -0.7007 0.04484 0.03556 -0.0151 1.0000 0.0496
-7.250 -0.6874 0.04233 0.03283 -0.0136 1.0000 0.0517
-7.000 -0.6724 0.03956 0.02969 -0.0118 1.0000 0.0533
-6.750 -0.6549 0.03689 0.02661 -0.0102 1.0000 0.0554
-6.500 -0.6350 0.03453 0.02376 -0.0087 1.0000 0.0591
-6.250 -0.6149 0.03263 0.02168 -0.0076 1.0000 0.0641
-6.000 -0.5920 0.03087 0.01972 -0.0065 1.0000 0.0694
-5.750 -0.5665 0.02908 0.01772 -0.0057 1.0000 0.0755
-5.500 -0.5439 0.02787 0.01637 -0.0047 1.0000 0.0863
-5.250 -0.5207 0.02653 0.01506 -0.0037 1.0000 0.0970
-5.000 -0.4991 0.02544 0.01393 -0.0025 1.0000 0.1151
-4.750 -0.4802 0.02429 0.01285 -0.0010 1.0000 0.1373
-4.500 -0.4633 0.02320 0.01190 0.0007 1.0000 0.1726
-4.250 -0.4487 0.02204 0.01104 0.0026 1.0000 0.2222
-4.000 -0.4368 0.02076 0.01025 0.0049 1.0000 0.2987
-3.750 -0.4328 0.01913 0.00978 0.0091 1.0000 0.4574
-3.500 -0.4003 0.01898 0.01067 0.0119 1.0000 0.7459
-3.250 -0.3645 0.01962 0.01108 0.0129 1.0000 0.8282
-3.000 -0.3265 0.02014 0.01129 0.0126 1.0000 0.8741
-2.750 -0.2773 0.02057 0.01137 0.0096 1.0000 0.9078
-2.500 -0.1823 0.02102 0.01128 -0.0017 1.0000 0.9475
-2.250 -0.0916 0.02078 0.01062 -0.0136 1.0000 0.9788
-2.000 -0.0522 0.02041 0.01008 -0.0170 1.0000 0.9892
-1.750 -0.0159 0.02006 0.00961 -0.0199 1.0000 0.9980
-1.500 -0.0027 0.01993 0.00943 -0.0185 1.0000 1.0000
-1.250 0.0001 0.01993 0.00940 -0.0153 1.0000 1.0000
-1.000 0.0002 0.01998 0.00943 -0.0117 1.0000 1.0000
-0.750 -0.0013 0.02008 0.00950 -0.0078 1.0000 1.0000
-0.500 0.0163 0.02018 0.00954 -0.0074 0.9941 1.0000
-0.250 0.0587 0.02022 0.00951 -0.0115 0.9801 1.0000
0.000 0.1016 0.02026 0.00951 -0.0155 0.9667 1.0000
0.250 0.1447 0.02029 0.00952 -0.0194 0.9535 1.0000
0.500 0.1869 0.02031 0.00956 -0.0230 0.9402 1.0000
0.750 0.2263 0.02033 0.00961 -0.0258 0.9261 1.0000
1.000 0.2632 0.02036 0.00969 -0.0281 0.9114 1.0000
1.250 0.2988 0.02037 0.00976 -0.0299 0.8956 1.0000
1.500 0.3340 0.02026 0.00970 -0.0310 0.8750 1.0000
1.750 0.3656 0.02004 0.00953 -0.0308 0.8488 1.0000
2.000 0.3897 0.01988 0.00937 -0.0292 0.8204 1.0000
2.250 0.4105 0.01981 0.00934 -0.0272 0.7936 1.0000
2.500 0.4308 0.01981 0.00938 -0.0254 0.7695 1.0000
2.750 0.4517 0.01979 0.00943 -0.0235 0.7458 1.0000
3.000 0.4720 0.01978 0.00947 -0.0216 0.7210 1.0000
3.250 0.4921 0.01980 0.00954 -0.0196 0.6949 1.0000
3.500 0.5124 0.01983 0.00961 -0.0176 0.6673 1.0000
3.750 0.5326 0.01989 0.00972 -0.0156 0.6373 1.0000
4.000 0.5526 0.01999 0.00982 -0.0135 0.6050 1.0000
4.250 0.5718 0.02017 0.01000 -0.0115 0.5681 1.0000
4.500 0.5908 0.02043 0.01021 -0.0094 0.5279 1.0000
4.750 0.6095 0.02079 0.01050 -0.0074 0.4844 1.0000
5.000 0.6278 0.02126 0.01091 -0.0054 0.4406 1.0000
5.250 0.6461 0.02184 0.01136 -0.0036 0.4031 1.0000
5.500 0.6649 0.02250 0.01193 -0.0020 0.3725 1.0000
5.750 0.6841 0.02320 0.01260 -0.0005 0.3477 1.0000
6.000 0.7040 0.02393 0.01334 0.0008 0.3277 1.0000
6.250 0.7244 0.02471 0.01422 0.0020 0.3102 1.0000
6.500 0.7446 0.02552 0.01511 0.0033 0.2933 1.0000
6.750 0.7624 0.02634 0.01593 0.0049 0.2724 1.0000
7.000 0.7752 0.02709 0.01667 0.0070 0.2437 1.0000
7.250 0.7866 0.02783 0.01746 0.0092 0.2139 1.0000
7.500 0.7985 0.02863 0.01837 0.0112 0.1848 1.0000
8.000 0.8188 0.03087 0.02064 0.0156 0.1085 1.0000
8.250 0.8282 0.03251 0.02207 0.0177 0.0840 1.0000
8.500 0.8383 0.03434 0.02385 0.0198 0.0720 1.0000
8.750 0.8483 0.03622 0.02575 0.0218 0.0635 1.0000
9.000 0.8578 0.03808 0.02766 0.0236 0.0569 1.0000
9.250 0.8698 0.04023 0.02997 0.0254 0.0531 1.0000
9.500 0.8833 0.04248 0.03252 0.0271 0.0498 1.0000
9.750 0.8932 0.04471 0.03493 0.0287 0.0466 1.0000
10.000 0.9010 0.04723 0.03744 0.0301 0.0438 1.0000
10.250 0.9056 0.04993 0.04059 0.0319 0.0418 1.0000
10.500 0.9058 0.05283 0.04386 0.0338 0.0405 1.0000
10.750 0.9019 0.05604 0.04740 0.0355 0.0398 1.0000
11.000 0.8939 0.05959 0.05124 0.0366 0.0393 1.0000
11.250 0.8820 0.06358 0.05551 0.0369 0.0391 1.0000
11.500 0.8667 0.06818 0.06036 0.0361 0.0390 1.0000
11.750 0.8482 0.07361 0.06601 0.0340 0.0391 1.0000
12.000 0.8272 0.08012 0.07270 0.0304 0.0394 1.0000
12.250 0.8042 0.08789 0.08063 0.0255 0.0399 1.0000
12.500 0.7808 0.09689 0.08967 0.0196 0.0406 1.0000
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Polar data table (+)
Polar graphs
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