GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.03 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiig-il-1000000.txt Download as CSV file: xf-giiig-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5947 0.11534 0.11374 0.0094 1.0000 0.0075
-10.250 -0.6054 0.10833 0.10676 0.0068 1.0000 0.0078
-10.000 -0.6047 0.10409 0.10253 0.0049 1.0000 0.0080
-7.250 -0.6144 0.03851 0.03614 -0.0255 1.0000 0.0077
-7.000 -0.6131 0.03006 0.02724 -0.0227 1.0000 0.0076
-6.750 -0.6105 0.02455 0.02121 -0.0192 1.0000 0.0076
-6.500 -0.5981 0.01948 0.01550 -0.0173 0.9984 0.0077
-6.250 -0.5712 0.01528 0.01070 -0.0180 0.9950 0.0080
-6.000 -0.5393 0.01433 0.00964 -0.0193 0.9916 0.0087
-5.750 -0.5067 0.01367 0.00889 -0.0207 0.9874 0.0094
-5.500 -0.4738 0.01268 0.00777 -0.0219 0.9832 0.0102
-5.250 -0.4434 0.01194 0.00692 -0.0226 0.9754 0.0110
-5.000 -0.4118 0.01142 0.00631 -0.0235 0.9675 0.0115
-4.750 -0.3857 0.01023 0.00494 -0.0232 0.9555 0.0122
-4.500 -0.3613 0.00943 0.00404 -0.0225 0.9415 0.0137
-4.250 -0.3355 0.00920 0.00377 -0.0220 0.9279 0.0153
-4.000 -0.3101 0.00891 0.00340 -0.0215 0.9144 0.0166
-3.750 -0.2843 0.00867 0.00308 -0.0210 0.9016 0.0175
-3.500 -0.2594 0.00816 0.00244 -0.0204 0.8896 0.0206
-3.250 -0.2330 0.00796 0.00222 -0.0201 0.8790 0.0250
-3.000 -0.2068 0.00772 0.00197 -0.0197 0.8691 0.0348
-2.750 -0.1802 0.00756 0.00179 -0.0195 0.8593 0.0448
-2.500 -0.1532 0.00743 0.00163 -0.0194 0.8504 0.0536
-2.250 -0.1262 0.00731 0.00150 -0.0192 0.8423 0.0643
-2.000 -0.0994 0.00713 0.00138 -0.0191 0.8338 0.0860
-1.750 -0.0731 0.00686 0.00127 -0.0189 0.8253 0.1381
-1.500 -0.0493 0.00624 0.00111 -0.0185 0.8157 0.2989
-1.250 -0.0317 0.00486 0.00090 -0.0171 0.8052 0.6590
-1.000 -0.0066 0.00468 0.00089 -0.0165 0.7956 0.7269
-0.750 0.0197 0.00462 0.00087 -0.0161 0.7866 0.7615
-0.500 0.0462 0.00456 0.00086 -0.0157 0.7768 0.7894
-0.250 0.0730 0.00452 0.00085 -0.0154 0.7677 0.8089
0.000 0.0995 0.00450 0.00084 -0.0150 0.7593 0.8304
0.250 0.1264 0.00447 0.00085 -0.0148 0.7506 0.8473
0.500 0.1526 0.00445 0.00087 -0.0143 0.7424 0.8686
0.750 0.1779 0.00442 0.00091 -0.0136 0.7336 0.8944
1.000 0.2047 0.00442 0.00093 -0.0133 0.7245 0.9072
1.250 0.2318 0.00444 0.00095 -0.0131 0.7154 0.9174
1.500 0.2588 0.00446 0.00097 -0.0128 0.7054 0.9282
1.750 0.2860 0.00449 0.00102 -0.0126 0.6946 0.9393
2.000 0.3136 0.00454 0.00105 -0.0125 0.6797 0.9495
2.250 0.3413 0.00466 0.00108 -0.0125 0.6473 0.9593
2.500 0.3696 0.00478 0.00113 -0.0126 0.6229 0.9690
2.750 0.4019 0.00494 0.00121 -0.0137 0.5903 0.9746
3.000 0.4309 0.00519 0.00129 -0.0141 0.5352 0.9823
3.250 0.4624 0.00587 0.00148 -0.0154 0.4116 0.9859
3.750 0.5262 0.00692 0.00192 -0.0182 0.2536 0.9936
4.000 0.5579 0.00770 0.00224 -0.0198 0.1449 0.9962
4.250 0.5901 0.00840 0.00259 -0.0214 0.0692 0.9989
4.500 0.6178 0.00880 0.00287 -0.0217 0.0415 1.0000
4.750 0.6397 0.00914 0.00316 -0.0207 0.0297 1.0000
5.000 0.6618 0.00951 0.00354 -0.0197 0.0235 1.0000
5.250 0.6850 0.00976 0.00382 -0.0189 0.0212 1.0000
5.500 0.7076 0.01012 0.00418 -0.0180 0.0187 1.0000
5.750 0.7277 0.01087 0.00504 -0.0165 0.0159 1.0000
6.000 0.7519 0.01106 0.00525 -0.0159 0.0151 1.0000
6.250 0.7755 0.01140 0.00563 -0.0152 0.0138 1.0000
6.500 0.7989 0.01179 0.00604 -0.0146 0.0126 1.0000
6.750 0.8207 0.01246 0.00675 -0.0136 0.0112 1.0000
7.000 0.8386 0.01382 0.00827 -0.0120 0.0102 1.0000
7.250 0.8631 0.01416 0.00865 -0.0116 0.0097 1.0000
7.500 0.8874 0.01453 0.00908 -0.0111 0.0089 1.0000
7.750 0.9114 0.01494 0.00952 -0.0107 0.0081 1.0000
8.000 0.9346 0.01549 0.01011 -0.0102 0.0076 1.0000
8.250 0.9555 0.01647 0.01116 -0.0093 0.0071 1.0000
8.500 0.9672 0.01959 0.01462 -0.0070 0.0065 1.0000
8.750 0.9899 0.02025 0.01539 -0.0065 0.0064 1.0000
9.000 1.0111 0.02123 0.01650 -0.0057 0.0062 1.0000
9.250 1.0309 0.02245 0.01791 -0.0048 0.0059 1.0000
9.500 1.0490 0.02395 0.01960 -0.0037 0.0055 1.0000
9.750 1.0654 0.02562 0.02148 -0.0025 0.0052 1.0000
10.000 1.0796 0.02754 0.02362 -0.0012 0.0050 1.0000
10.250 1.0894 0.03002 0.02638 0.0006 0.0048 1.0000
10.500 1.0899 0.03370 0.03044 0.0031 0.0047 1.0000
10.750 0.9812 0.05165 0.04953 0.0120 0.0053 1.0000
11.000 0.9485 0.05830 0.05641 0.0115 0.0055 1.0000
11.250 0.9221 0.06527 0.06353 0.0081 0.0056 1.0000
11.500 0.8978 0.07370 0.07210 0.0019 0.0056 1.0000
12.000 0.8347 0.10637 0.10487 -0.0199 0.0060 1.0000
12.250 0.8149 0.11644 0.11491 -0.0248 0.0063 1.0000
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Polar data table (+)
Polar graphs
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