GIII BL288 AIRFOIL (giiii-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL288 AIRFOIL (giiii-il) Reynolds number: 1,000,000 Max Cl/Cd: 79.16 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiii-il-1000000.txt Download as CSV file: xf-giiii-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL288 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4750 0.09612 0.09457 -0.0084 1.0000 0.0128
-10.000 -0.4902 0.08879 0.08725 -0.0104 1.0000 0.0130
-9.750 -0.4917 0.08484 0.08332 -0.0114 1.0000 0.0132
-9.500 -0.4921 0.08114 0.07961 -0.0124 1.0000 0.0134
-9.250 -0.4945 0.07690 0.07539 -0.0138 1.0000 0.0135
-9.000 -0.4987 0.07231 0.07081 -0.0157 1.0000 0.0137
-8.750 -0.5061 0.06724 0.06575 -0.0184 1.0000 0.0138
-8.500 -0.5340 0.05885 0.05736 -0.0266 1.0000 0.0136
-8.250 -0.5493 0.05356 0.05201 -0.0286 1.0000 0.0136
-8.000 -0.5513 0.04925 0.04763 -0.0296 1.0000 0.0138
-7.750 -0.5501 0.04508 0.04338 -0.0302 1.0000 0.0141
-7.500 -0.5473 0.04075 0.03895 -0.0304 1.0000 0.0145
-7.250 -0.5429 0.03638 0.03446 -0.0300 1.0000 0.0153
-7.000 -0.5321 0.03161 0.02942 -0.0285 1.0000 0.0170
-6.750 -0.6137 0.02490 0.02134 -0.0182 1.0000 0.0130
-6.500 -0.5914 0.02028 0.01622 -0.0187 0.9973 0.0135
-6.250 -0.5564 0.02134 0.01740 -0.0207 0.9955 0.0140
-6.000 -0.5271 0.01864 0.01437 -0.0216 0.9926 0.0145
-5.750 -0.4975 0.01604 0.01142 -0.0222 0.9891 0.0150
-5.500 -0.4655 0.01433 0.00949 -0.0233 0.9862 0.0154
-5.250 -0.4329 0.01303 0.00802 -0.0245 0.9834 0.0158
-5.000 -0.4038 0.01211 0.00698 -0.0248 0.9766 0.0163
-4.750 -0.3720 0.01158 0.00638 -0.0257 0.9711 0.0168
-4.500 -0.3459 0.01040 0.00509 -0.0254 0.9617 0.0178
-4.250 -0.3189 0.00989 0.00454 -0.0253 0.9519 0.0187
-4.000 -0.2928 0.00959 0.00420 -0.0248 0.9407 0.0195
-3.750 -0.2674 0.00928 0.00385 -0.0242 0.9286 0.0205
-3.500 -0.2417 0.00901 0.00353 -0.0237 0.9172 0.0216
-3.250 -0.2155 0.00884 0.00331 -0.0233 0.9063 0.0225
-3.000 -0.1910 0.00828 0.00267 -0.0226 0.8957 0.0250
-2.750 -0.1643 0.00815 0.00253 -0.0223 0.8857 0.0272
-2.500 -0.1373 0.00803 0.00239 -0.0221 0.8766 0.0294
-2.250 -0.1111 0.00780 0.00208 -0.0217 0.8669 0.0315
-2.000 -0.0847 0.00757 0.00182 -0.0213 0.8557 0.0351
-1.750 -0.0577 0.00747 0.00169 -0.0211 0.8447 0.0382
-1.500 -0.0305 0.00740 0.00160 -0.0209 0.8349 0.0401
-1.250 -0.0037 0.00720 0.00135 -0.0206 0.8252 0.0464
-1.000 0.0236 0.00709 0.00123 -0.0205 0.8151 0.0522
-0.750 0.0494 0.00672 0.00109 -0.0201 0.8049 0.1377
-0.500 0.0640 0.00483 0.00087 -0.0184 0.7941 0.6646
-0.250 0.0876 0.00456 0.00090 -0.0174 0.7829 0.7685
0.000 0.1125 0.00444 0.00092 -0.0165 0.7717 0.8174
0.250 0.1384 0.00439 0.00092 -0.0159 0.7602 0.8455
0.500 0.1649 0.00439 0.00092 -0.0155 0.7480 0.8635
0.750 0.1913 0.00439 0.00093 -0.0150 0.7351 0.8820
1.000 0.2173 0.00440 0.00095 -0.0144 0.7211 0.9007
1.250 0.2423 0.00441 0.00100 -0.0136 0.7060 0.9258
1.500 0.2686 0.00447 0.00103 -0.0131 0.6866 0.9402
1.750 0.2959 0.00458 0.00106 -0.0128 0.6588 0.9507
2.000 0.3243 0.00471 0.00109 -0.0129 0.6289 0.9604
2.250 0.3530 0.00485 0.00115 -0.0131 0.5996 0.9703
2.500 0.3846 0.00514 0.00121 -0.0140 0.5385 0.9762
2.750 0.4144 0.00547 0.00131 -0.0146 0.4795 0.9836
3.000 0.4490 0.00576 0.00143 -0.0163 0.4331 0.9867
3.250 0.4829 0.00610 0.00156 -0.0180 0.3768 0.9903
3.500 0.5149 0.00652 0.00172 -0.0192 0.3155 0.9942
3.750 0.5488 0.00697 0.00190 -0.0210 0.2498 0.9966
4.000 0.5820 0.00747 0.00213 -0.0226 0.1858 0.9991
4.250 0.6078 0.00798 0.00237 -0.0227 0.1264 1.0000
4.500 0.6294 0.00840 0.00261 -0.0216 0.0896 1.0000
4.750 0.6518 0.00874 0.00284 -0.0207 0.0686 1.0000
5.000 0.6746 0.00907 0.00310 -0.0199 0.0533 1.0000
5.250 0.6982 0.00932 0.00332 -0.0191 0.0466 1.0000
5.500 0.7217 0.00962 0.00361 -0.0183 0.0407 1.0000
5.750 0.7457 0.00986 0.00385 -0.0177 0.0375 1.0000
6.000 0.7688 0.01025 0.00424 -0.0169 0.0329 1.0000
6.250 0.7931 0.01053 0.00455 -0.0163 0.0310 1.0000
6.500 0.8178 0.01078 0.00482 -0.0158 0.0289 1.0000
6.750 0.8418 0.01115 0.00516 -0.0152 0.0260 1.0000
7.000 0.8650 0.01165 0.00573 -0.0145 0.0236 1.0000
7.250 0.8900 0.01192 0.00603 -0.0141 0.0223 1.0000
7.500 0.9147 0.01225 0.00638 -0.0137 0.0208 1.0000
7.750 0.9382 0.01275 0.00687 -0.0131 0.0189 1.0000
8.000 0.9607 0.01339 0.00760 -0.0124 0.0176 1.0000
8.250 0.9853 0.01374 0.00800 -0.0120 0.0168 1.0000
8.500 1.0094 0.01416 0.00845 -0.0115 0.0159 1.0000
8.750 1.0333 0.01459 0.00891 -0.0111 0.0150 1.0000
9.000 1.0557 0.01522 0.00957 -0.0105 0.0141 1.0000
9.250 1.0748 0.01632 0.01079 -0.0094 0.0131 1.0000
9.500 1.0988 0.01671 0.01123 -0.0090 0.0127 1.0000
9.750 1.1214 0.01727 0.01186 -0.0084 0.0121 1.0000
10.000 1.1437 0.01786 0.01252 -0.0078 0.0116 1.0000
10.250 1.1657 0.01844 0.01315 -0.0072 0.0110 1.0000
10.500 1.1868 0.01912 0.01389 -0.0065 0.0106 1.0000
10.750 1.2023 0.02053 0.01542 -0.0052 0.0099 1.0000
11.000 1.2160 0.02215 0.01723 -0.0036 0.0096 1.0000
11.250 1.2360 0.02285 0.01802 -0.0029 0.0093 1.0000
11.500 1.2548 0.02363 0.01890 -0.0020 0.0090 1.0000
11.750 1.2726 0.02446 0.01984 -0.0010 0.0087 1.0000
12.000 1.2893 0.02534 0.02081 0.0000 0.0083 1.0000
12.250 1.3046 0.02627 0.02185 0.0012 0.0080 1.0000
12.500 1.3177 0.02725 0.02292 0.0026 0.0078 1.0000
12.750 1.3275 0.02832 0.02407 0.0044 0.0076 1.0000
13.000 1.3329 0.02973 0.02559 0.0064 0.0074 1.0000
13.250 1.3310 0.03183 0.02784 0.0086 0.0072 1.0000
13.500 1.3189 0.03508 0.03132 0.0108 0.0070 1.0000
14.000 1.2901 0.04316 0.03987 0.0120 0.0068 1.0000
14.250 1.2860 0.04653 0.04340 0.0113 0.0068 1.0000
14.500 1.2780 0.05071 0.04773 0.0098 0.0067 1.0000
14.750 1.2657 0.05593 0.05313 0.0073 0.0067 1.0000
15.000 1.2490 0.06238 0.05975 0.0037 0.0067 1.0000
15.250 1.2275 0.07038 0.06793 -0.0012 0.0067 1.0000
15.500 1.1971 0.08067 0.07840 -0.0076 0.0067 1.0000
15.750 1.1498 0.09504 0.09297 -0.0161 0.0068 1.0000
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