GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 50,000 Max Cl/Cd: 31.02 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiic-il-50000-n5.txt Download as CSV file: xf-giiic-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6158 0.09536 0.08869 -0.0103 1.0000 0.0482
-9.500 -0.6224 0.08888 0.08225 -0.0152 1.0000 0.0475
-9.250 -0.6333 0.08267 0.07606 -0.0195 1.0000 0.0467
-9.000 -0.6471 0.07722 0.07059 -0.0220 1.0000 0.0461
-8.750 -0.6606 0.07225 0.06553 -0.0229 1.0000 0.0455
-8.500 -0.6705 0.06731 0.06041 -0.0233 1.0000 0.0451
-8.250 -0.6763 0.06259 0.05546 -0.0230 1.0000 0.0448
-8.000 -0.6784 0.05807 0.05064 -0.0222 1.0000 0.0447
-7.750 -0.6766 0.05381 0.04602 -0.0210 1.0000 0.0449
-7.500 -0.6713 0.04983 0.04164 -0.0195 1.0000 0.0453
-7.250 -0.6625 0.04624 0.03763 -0.0180 1.0000 0.0464
-7.000 -0.6511 0.04306 0.03390 -0.0164 1.0000 0.0490
-6.750 -0.6373 0.03990 0.03010 -0.0146 1.0000 0.0517
-6.500 -0.6200 0.03689 0.02662 -0.0130 1.0000 0.0534
-6.250 -0.6003 0.03445 0.02399 -0.0120 1.0000 0.0556
-6.000 -0.5787 0.03234 0.02163 -0.0109 1.0000 0.0588
-5.750 -0.5559 0.03056 0.01941 -0.0098 1.0000 0.0651
-5.500 -0.5337 0.02894 0.01782 -0.0089 1.0000 0.0714
-5.250 -0.5076 0.02733 0.01585 -0.0080 1.0000 0.0786
-5.000 -0.4856 0.02616 0.01469 -0.0070 1.0000 0.0913
-4.750 -0.4632 0.02495 0.01342 -0.0059 1.0000 0.1059
-4.500 -0.4444 0.02385 0.01246 -0.0045 1.0000 0.1284
-4.250 -0.4271 0.02276 0.01148 -0.0028 1.0000 0.1606
-4.000 -0.4123 0.02166 0.01067 -0.0010 1.0000 0.2090
-3.750 -0.4006 0.02047 0.00989 0.0012 1.0000 0.2830
-3.500 -0.3954 0.01885 0.00931 0.0048 1.0000 0.4320
-3.250 -0.3668 0.01852 0.01027 0.0088 1.0000 0.7726
-3.000 -0.3335 0.01906 0.01057 0.0099 1.0000 0.8549
-2.750 -0.2833 0.01962 0.01071 0.0075 1.0000 0.9077
-2.500 -0.1822 0.02003 0.01052 -0.0048 1.0000 0.9517
-2.250 -0.0649 0.01960 0.00951 -0.0215 1.0000 0.9922
-2.000 -0.0311 0.01929 0.00904 -0.0240 1.0000 1.0000
-1.750 -0.0251 0.01925 0.00895 -0.0214 1.0000 1.0000
-1.500 -0.0239 0.01929 0.00892 -0.0179 1.0000 1.0000
-1.250 -0.0251 0.01937 0.00896 -0.0141 1.0000 1.0000
-1.000 -0.0271 0.01948 0.00901 -0.0102 1.0000 1.0000
-0.750 0.0090 0.01951 0.00892 -0.0131 0.9881 1.0000
-0.500 0.0477 0.01956 0.00888 -0.0164 0.9765 1.0000
-0.250 0.0867 0.01961 0.00885 -0.0196 0.9652 1.0000
0.000 0.1256 0.01968 0.00887 -0.0227 0.9541 1.0000
0.250 0.1637 0.01975 0.00892 -0.0256 0.9429 1.0000
0.500 0.2012 0.01982 0.00899 -0.0282 0.9317 1.0000
0.750 0.2382 0.01991 0.00909 -0.0305 0.9205 1.0000
1.000 0.2712 0.02002 0.00925 -0.0320 0.9081 1.0000
1.250 0.3013 0.02015 0.00944 -0.0329 0.8949 1.0000
1.500 0.3310 0.02028 0.00962 -0.0334 0.8808 1.0000
1.750 0.3607 0.02032 0.00972 -0.0335 0.8638 1.0000
2.000 0.3844 0.02034 0.00982 -0.0322 0.8419 1.0000
2.250 0.4092 0.02028 0.00980 -0.0307 0.8210 1.0000
2.500 0.4287 0.02034 0.00993 -0.0287 0.7997 1.0000
2.750 0.4501 0.02036 0.01006 -0.0269 0.7810 1.0000
3.000 0.4696 0.02042 0.01021 -0.0249 0.7611 1.0000
3.250 0.4894 0.02044 0.01034 -0.0229 0.7405 1.0000
3.500 0.5096 0.02043 0.01043 -0.0209 0.7194 1.0000
3.750 0.5295 0.02042 0.01053 -0.0188 0.6962 1.0000
4.000 0.5494 0.02042 0.01068 -0.0166 0.6707 1.0000
4.250 0.5696 0.02041 0.01077 -0.0145 0.6426 1.0000
4.500 0.5900 0.02041 0.01085 -0.0123 0.6108 1.0000
4.750 0.6099 0.02049 0.01098 -0.0101 0.5737 1.0000
5.000 0.6294 0.02066 0.01115 -0.0078 0.5314 1.0000
5.250 0.6481 0.02098 0.01146 -0.0056 0.4839 1.0000
5.500 0.6661 0.02147 0.01184 -0.0035 0.4348 1.0000
5.750 0.6834 0.02212 0.01235 -0.0014 0.3897 1.0000
6.000 0.7000 0.02292 0.01299 0.0006 0.3491 1.0000
6.250 0.7148 0.02386 0.01372 0.0026 0.3081 1.0000
6.750 0.7416 0.02589 0.01557 0.0063 0.2197 1.0000
7.000 0.7546 0.02703 0.01664 0.0081 0.1738 1.0000
7.250 0.7660 0.02850 0.01788 0.0100 0.1272 1.0000
7.500 0.7782 0.03021 0.01936 0.0118 0.0956 1.0000
7.750 0.7920 0.03195 0.02106 0.0135 0.0788 1.0000
8.000 0.8069 0.03372 0.02288 0.0152 0.0684 1.0000
8.250 0.8209 0.03554 0.02466 0.0166 0.0603 1.0000
8.500 0.8400 0.03751 0.02702 0.0180 0.0550 1.0000
8.750 0.8576 0.03965 0.02928 0.0193 0.0512 1.0000
9.000 0.8738 0.04215 0.03194 0.0205 0.0476 1.0000
9.250 0.8874 0.04465 0.03488 0.0218 0.0440 1.0000
9.500 0.8984 0.04743 0.03800 0.0232 0.0418 1.0000
9.750 0.9064 0.05048 0.04137 0.0247 0.0405 1.0000
10.000 0.9103 0.05368 0.04487 0.0261 0.0396 1.0000
10.250 0.9102 0.05704 0.04851 0.0276 0.0389 1.0000
10.500 0.9055 0.06044 0.05213 0.0290 0.0383 1.0000
10.750 0.8964 0.06404 0.05592 0.0303 0.0378 1.0000
11.750 0.8125 0.08613 0.07898 0.0222 0.0391 1.0000
12.000 0.7700 0.09950 0.09250 0.0120 0.0412 1.0000
12.250 0.7463 0.11095 0.10392 0.0049 0.0425 1.0000
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Polar data table (+)
Polar graphs
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