GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 50,000 Max Cl/Cd: 30.15 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiic-il-50000.txt Download as CSV file: xf-giiic-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5588 0.09610 0.08962 0.0176 1.0000 0.3581
-8.000 -0.5487 0.09248 0.08602 0.0187 1.0000 0.3789
-7.500 -0.5471 0.08624 0.07990 0.0215 1.0000 0.4282
-7.250 -0.6385 0.06620 0.05959 -0.0157 1.0000 0.1791
-7.000 -0.6416 0.05798 0.05067 -0.0180 1.0000 0.1374
-6.750 -0.6391 0.05282 0.04479 -0.0169 1.0000 0.1257
-6.500 -0.6272 0.04886 0.04053 -0.0156 1.0000 0.1249
-6.250 -0.6143 0.04514 0.03645 -0.0140 1.0000 0.1241
-6.000 -0.5997 0.04156 0.03247 -0.0122 1.0000 0.1227
-5.750 -0.5838 0.03829 0.02872 -0.0102 1.0000 0.1222
-5.500 -0.5663 0.03548 0.02537 -0.0082 1.0000 0.1245
-5.250 -0.5475 0.03310 0.02283 -0.0067 1.0000 0.1325
-5.000 -0.5268 0.03092 0.02011 -0.0048 1.0000 0.1398
-4.750 -0.5039 0.02872 0.01785 -0.0036 1.0000 0.1518
-4.500 -0.4806 0.02680 0.01590 -0.0024 1.0000 0.1721
-4.250 -0.4545 0.02489 0.01412 -0.0014 1.0000 0.2048
-4.000 -0.4276 0.02276 0.01231 -0.0006 1.0000 0.2689
-3.750 -0.1493 0.02174 0.01256 -0.0282 1.0000 1.0000
-3.500 -0.1304 0.02118 0.01177 -0.0282 1.0000 1.0000
-3.250 -0.1115 0.02069 0.01108 -0.0281 1.0000 1.0000
-3.000 -0.0928 0.02028 0.01047 -0.0278 1.0000 1.0000
-2.750 -0.0748 0.01993 0.00997 -0.0273 1.0000 1.0000
-2.500 -0.0579 0.01964 0.00956 -0.0266 1.0000 1.0000
-2.250 -0.0429 0.01942 0.00925 -0.0256 1.0000 1.0000
-2.000 -0.0312 0.01928 0.00904 -0.0240 1.0000 1.0000
-1.750 -0.0248 0.01923 0.00892 -0.0214 1.0000 1.0000
-1.500 -0.0233 0.01927 0.00891 -0.0180 1.0000 1.0000
-1.250 -0.0244 0.01935 0.00894 -0.0142 1.0000 1.0000
-1.000 -0.0264 0.01946 0.00899 -0.0103 1.0000 1.0000
-0.750 -0.0281 0.01957 0.00905 -0.0064 1.0000 1.0000
-0.500 -0.0288 0.01970 0.00912 -0.0027 1.0000 1.0000
-0.250 -0.0282 0.01985 0.00921 0.0008 1.0000 1.0000
0.000 -0.0258 0.02003 0.00932 0.0040 1.0000 1.0000
0.250 -0.0215 0.02024 0.00945 0.0067 1.0000 1.0000
0.500 -0.0154 0.02050 0.00964 0.0092 1.0000 1.0000
0.750 -0.0072 0.02080 0.00988 0.0113 1.0000 1.0000
1.000 0.0029 0.02116 0.01018 0.0129 1.0000 1.0000
1.250 0.0146 0.02157 0.01054 0.0143 1.0000 1.0000
1.500 0.0277 0.02203 0.01097 0.0153 1.0000 1.0000
1.750 0.0416 0.02254 0.01146 0.0161 1.0000 1.0000
2.000 0.0563 0.02311 0.01202 0.0167 1.0000 1.0000
2.250 0.1126 0.02430 0.01328 0.0093 0.9843 1.0000
2.500 0.1783 0.02545 0.01459 0.0007 0.9605 1.0000
2.750 0.2420 0.02642 0.01573 -0.0071 0.9368 1.0000
3.000 0.3118 0.02717 0.01676 -0.0153 0.9119 1.0000
3.250 0.3705 0.02764 0.01750 -0.0210 0.8852 1.0000
3.500 0.4400 0.02776 0.01802 -0.0277 0.8570 1.0000
3.750 0.4999 0.02753 0.01815 -0.0316 0.8276 1.0000
4.000 0.5431 0.02717 0.01810 -0.0319 0.7962 1.0000
4.250 0.5740 0.02675 0.01797 -0.0299 0.7616 1.0000
4.500 0.6086 0.02574 0.01719 -0.0272 0.7264 1.0000
4.750 0.6328 0.02490 0.01651 -0.0231 0.6852 1.0000
5.000 0.6555 0.02410 0.01579 -0.0187 0.6391 1.0000
5.250 0.6767 0.02367 0.01536 -0.0147 0.5889 1.0000
5.500 0.6976 0.02364 0.01520 -0.0112 0.5395 1.0000
5.750 0.7164 0.02401 0.01546 -0.0081 0.4908 1.0000
6.000 0.7339 0.02434 0.01555 -0.0049 0.4413 1.0000
6.250 0.7474 0.02483 0.01576 -0.0015 0.3864 1.0000
6.500 0.7588 0.02581 0.01646 0.0017 0.3263 1.0000
6.750 0.7672 0.02774 0.01792 0.0051 0.2512 1.0000
7.000 0.7776 0.03010 0.01973 0.0082 0.1859 1.0000
7.250 0.7937 0.03217 0.02171 0.0103 0.1500 1.0000
7.500 0.8149 0.03455 0.02402 0.0118 0.1303 1.0000
7.750 0.8345 0.03692 0.02653 0.0132 0.1166 1.0000
8.000 0.8546 0.03990 0.02989 0.0147 0.1095 1.0000
8.250 0.8720 0.04318 0.03342 0.0160 0.1042 1.0000
8.500 0.8810 0.04658 0.03744 0.0181 0.1001 1.0000
8.750 0.8906 0.04993 0.04115 0.0198 0.0966 1.0000
9.000 0.8944 0.05410 0.04578 0.0217 0.0961 1.0000
9.250 0.8892 0.05887 0.05104 0.0235 0.0972 1.0000
9.500 0.8778 0.06389 0.05646 0.0249 0.0988 1.0000
9.750 0.8613 0.06894 0.06180 0.0257 0.1005 1.0000
10.000 0.8432 0.07386 0.06688 0.0261 0.1022 1.0000
10.250 0.8260 0.07874 0.07184 0.0260 0.1037 1.0000
10.500 0.8194 0.08394 0.07706 0.0253 0.1051 1.0000
10.750 0.6131 0.09388 0.08722 0.0176 0.1282 1.0000
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Polar data table (+)
Polar graphs
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