GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 50,000 Max Cl/Cd: 31.94 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiig-il-50000.txt Download as CSV file: xf-giiig-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5627 0.09857 0.09205 0.0044 1.0000 0.2533
-8.000 -0.5666 0.09537 0.08893 0.0039 1.0000 0.2693
-7.750 -0.5778 0.09247 0.08615 0.0026 1.0000 0.2850
-7.500 -0.5521 0.08819 0.08179 0.0076 1.0000 0.3198
-7.250 -0.5551 0.08561 0.07929 0.0096 1.0000 0.3541
-7.000 -0.5351 0.08250 0.07617 0.0153 1.0000 0.4090
-6.750 -0.5064 0.07934 0.07297 0.0214 1.0000 0.4760
-6.500 -0.4747 0.07657 0.07015 0.0278 1.0000 0.5618
-6.250 -0.4277 0.07323 0.06665 0.0333 1.0000 0.6747
-5.500 -0.4397 0.06290 0.05659 0.0293 1.0000 0.6236
-5.250 -0.5183 0.05739 0.05153 0.0167 1.0000 0.4971
-5.000 -0.4796 0.04340 0.03487 -0.0209 1.0000 0.1574
-4.750 -0.4584 0.03961 0.03061 -0.0197 1.0000 0.1398
-4.500 -0.4366 0.03669 0.02696 -0.0181 1.0000 0.1298
-4.250 -0.4162 0.03437 0.02407 -0.0164 1.0000 0.1312
-4.000 -0.3949 0.03154 0.02108 -0.0153 1.0000 0.1339
-3.750 -0.3710 0.02921 0.01838 -0.0139 1.0000 0.1347
-3.500 -0.3468 0.02725 0.01609 -0.0127 1.0000 0.1411
-3.250 -0.3226 0.02553 0.01419 -0.0116 1.0000 0.1560
-3.000 -0.2941 0.02374 0.01230 -0.0107 1.0000 0.1709
-2.750 -0.0948 0.01783 0.00870 -0.0308 1.0000 1.0000
-2.500 -0.0792 0.01762 0.00820 -0.0294 1.0000 1.0000
-2.250 -0.0661 0.01744 0.00781 -0.0276 1.0000 1.0000
-2.000 -0.0564 0.01731 0.00753 -0.0252 1.0000 1.0000
-1.750 -0.0505 0.01723 0.00733 -0.0221 1.0000 1.0000
-1.500 -0.0476 0.01719 0.00715 -0.0186 1.0000 1.0000
-1.250 -0.0465 0.01719 0.00705 -0.0148 1.0000 1.0000
-1.000 -0.0450 0.01723 0.00697 -0.0111 1.0000 1.0000
-0.750 -0.0414 0.01729 0.00691 -0.0077 1.0000 1.0000
-0.500 -0.0347 0.01739 0.00687 -0.0049 1.0000 1.0000
-0.250 -0.0244 0.01753 0.00688 -0.0027 1.0000 1.0000
0.000 -0.0114 0.01771 0.00693 -0.0010 1.0000 1.0000
0.250 0.0036 0.01794 0.00702 0.0002 1.0000 1.0000
0.500 0.0200 0.01820 0.00718 0.0012 1.0000 1.0000
0.750 0.0374 0.01850 0.00740 0.0020 1.0000 1.0000
1.000 0.0554 0.01883 0.00767 0.0027 1.0000 1.0000
1.250 0.0739 0.01921 0.00800 0.0032 1.0000 1.0000
1.500 0.0927 0.01962 0.00839 0.0035 1.0000 1.0000
1.750 0.1118 0.02008 0.00883 0.0038 1.0000 1.0000
2.000 0.1309 0.02058 0.00934 0.0040 1.0000 1.0000
2.250 0.1500 0.02113 0.00991 0.0041 1.0000 1.0000
2.500 0.1689 0.02173 0.01055 0.0041 1.0000 1.0000
2.750 0.1878 0.02239 0.01130 0.0040 1.0000 1.0000
3.000 0.2063 0.02312 0.01210 0.0039 1.0000 1.0000
3.250 0.2547 0.02434 0.01351 -0.0021 0.9861 1.0000
3.500 0.3153 0.02566 0.01511 -0.0101 0.9635 1.0000
3.750 0.3766 0.02683 0.01667 -0.0177 0.9385 1.0000
4.000 0.4345 0.02774 0.01798 -0.0240 0.9103 1.0000
4.250 0.4904 0.02835 0.01910 -0.0290 0.8783 1.0000
4.500 0.5815 0.02705 0.01864 -0.0355 0.8275 1.0000
4.750 0.6406 0.02299 0.01517 -0.0295 0.7492 1.0000
5.000 0.6599 0.02066 0.01311 -0.0207 0.6630 1.0000
5.250 0.6517 0.02131 0.01168 -0.0086 0.3239 1.0000
5.500 0.6584 0.02467 0.01363 -0.0052 0.1961 1.0000
5.750 0.6826 0.02696 0.01563 -0.0037 0.1582 1.0000
6.000 0.7115 0.02929 0.01777 -0.0030 0.1360 1.0000
6.250 0.7409 0.03184 0.02037 -0.0025 0.1229 1.0000
6.500 0.7689 0.03458 0.02362 -0.0015 0.1174 1.0000
6.750 0.7936 0.03786 0.02696 -0.0009 0.1108 1.0000
7.000 0.8128 0.04068 0.03050 0.0008 0.1064 1.0000
7.250 0.8313 0.04441 0.03477 0.0023 0.1067 1.0000
7.500 0.8467 0.04856 0.03942 0.0037 0.1085 1.0000
7.750 0.8628 0.05334 0.04446 0.0047 0.1109 1.0000
8.000 0.8604 0.05811 0.05029 0.0066 0.1190 1.0000
8.250 0.8683 0.06330 0.05571 0.0073 0.1232 1.0000
8.500 0.8564 0.06950 0.06250 0.0071 0.1349 1.0000
8.750 0.8474 0.07650 0.06978 0.0057 0.1499 1.0000
9.000 0.8041 0.08479 0.07831 -0.0001 0.1701 1.0000
9.250 0.7595 0.09815 0.09154 -0.0148 0.2163 1.0000
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Polar data table (+)
Polar graphs
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