GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 1,000,000 Max Cl/Cd: 72.45 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiif-il-1000000-n5.txt Download as CSV file: xf-giiif-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL145 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6132 0.09705 0.09550 0.0024 1.0000 0.0030
-9.500 -0.6207 0.09055 0.08903 -0.0012 1.0000 0.0029
-8.500 -0.7793 0.02278 0.01933 -0.0219 1.0000 0.0025
-8.250 -0.7707 0.01825 0.01412 -0.0194 1.0000 0.0027
-8.000 -0.7503 0.01636 0.01193 -0.0186 0.9984 0.0029
-7.750 -0.7210 0.01537 0.01079 -0.0194 0.9931 0.0031
-7.500 -0.6908 0.01464 0.00996 -0.0204 0.9868 0.0033
-7.250 -0.6610 0.01395 0.00915 -0.0212 0.9789 0.0036
-7.000 -0.6312 0.01326 0.00835 -0.0220 0.9696 0.0039
-6.750 -0.6022 0.01259 0.00756 -0.0225 0.9576 0.0041
-6.500 -0.5752 0.01202 0.00684 -0.0225 0.9427 0.0044
-6.250 -0.5498 0.01155 0.00624 -0.0220 0.9266 0.0046
-6.000 -0.5248 0.01113 0.00571 -0.0215 0.9112 0.0048
-5.750 -0.5004 0.01053 0.00499 -0.0209 0.8965 0.0056
-5.500 -0.4747 0.01030 0.00471 -0.0206 0.8827 0.0064
-5.250 -0.4487 0.01007 0.00441 -0.0203 0.8701 0.0072
-5.000 -0.4226 0.00981 0.00406 -0.0200 0.8587 0.0078
-4.750 -0.3961 0.00959 0.00376 -0.0198 0.8488 0.0082
-4.500 -0.3706 0.00912 0.00318 -0.0194 0.8396 0.0097
-4.250 -0.3443 0.00888 0.00289 -0.0192 0.8304 0.0109
-4.000 -0.3175 0.00869 0.00265 -0.0191 0.8221 0.0123
-3.750 -0.2908 0.00851 0.00241 -0.0189 0.8141 0.0134
-3.500 -0.2638 0.00831 0.00215 -0.0188 0.8068 0.0148
-3.250 -0.2371 0.00810 0.00192 -0.0186 0.8001 0.0204
-3.000 -0.2099 0.00792 0.00174 -0.0185 0.7933 0.0277
-2.500 -0.1556 0.00764 0.00147 -0.0184 0.7800 0.0457
-2.250 -0.1284 0.00752 0.00134 -0.0184 0.7738 0.0560
-2.000 -0.1009 0.00739 0.00124 -0.0184 0.7681 0.0673
-1.750 -0.0736 0.00728 0.00115 -0.0184 0.7612 0.0823
-1.500 -0.0464 0.00717 0.00106 -0.0183 0.7519 0.0993
-1.250 -0.0195 0.00703 0.00097 -0.0182 0.7408 0.1294
-1.000 0.0072 0.00686 0.00090 -0.0182 0.7302 0.1730
-0.750 0.0330 0.00648 0.00081 -0.0180 0.7202 0.2784
-0.500 0.0522 0.00522 0.00063 -0.0170 0.7104 0.6279
-0.250 0.0782 0.00505 0.00062 -0.0166 0.7003 0.6881
0.000 0.1044 0.00496 0.00062 -0.0163 0.6890 0.7324
0.250 0.1311 0.00491 0.00063 -0.0160 0.6766 0.7616
0.500 0.1581 0.00490 0.00063 -0.0159 0.6645 0.7803
0.750 0.1848 0.00487 0.00066 -0.0156 0.6532 0.8049
1.000 0.2115 0.00486 0.00068 -0.0154 0.6422 0.8268
1.250 0.2383 0.00487 0.00072 -0.0151 0.6308 0.8435
1.500 0.2656 0.00490 0.00075 -0.0151 0.6189 0.8529
1.750 0.2930 0.00495 0.00080 -0.0150 0.6066 0.8610
2.250 0.3451 0.00531 0.00091 -0.0144 0.5146 0.8799
2.500 0.3670 0.00603 0.00112 -0.0136 0.3752 0.8912
2.750 0.3928 0.00626 0.00126 -0.0134 0.3361 0.9024
3.000 0.4185 0.00651 0.00140 -0.0131 0.2960 0.9146
3.250 0.4424 0.00702 0.00161 -0.0126 0.2126 0.9280
3.500 0.4671 0.00750 0.00184 -0.0123 0.1427 0.9414
3.750 0.4934 0.00792 0.00210 -0.0122 0.0932 0.9539
4.000 0.5216 0.00825 0.00232 -0.0126 0.0623 0.9650
4.250 0.5518 0.00857 0.00255 -0.0134 0.0409 0.9734
4.500 0.5828 0.00883 0.00278 -0.0143 0.0303 0.9802
4.750 0.6134 0.00908 0.00303 -0.0152 0.0243 0.9865
5.000 0.6451 0.00935 0.00329 -0.0163 0.0192 0.9911
5.250 0.6759 0.00961 0.00356 -0.0172 0.0167 0.9956
5.500 0.7073 0.00993 0.00387 -0.0183 0.0139 0.9989
5.750 0.7331 0.01029 0.00427 -0.0181 0.0116 1.0000
6.250 0.7809 0.01080 0.00486 -0.0169 0.0100 1.0000
6.500 0.8049 0.01111 0.00518 -0.0164 0.0088 1.0000
6.750 0.8285 0.01151 0.00558 -0.0158 0.0076 1.0000
7.000 0.8521 0.01195 0.00607 -0.0152 0.0067 1.0000
7.250 0.8765 0.01226 0.00642 -0.0148 0.0060 1.0000
7.500 0.9006 0.01264 0.00682 -0.0143 0.0053 1.0000
7.750 0.9244 0.01307 0.00727 -0.0139 0.0047 1.0000
8.000 0.9468 0.01373 0.00803 -0.0132 0.0040 1.0000
8.250 0.9696 0.01433 0.00871 -0.0125 0.0038 1.0000
8.500 0.9927 0.01488 0.00934 -0.0120 0.0036 1.0000
8.750 1.0153 0.01549 0.01004 -0.0114 0.0034 1.0000
9.000 1.0376 0.01615 0.01078 -0.0108 0.0032 1.0000
9.250 1.0597 0.01683 0.01155 -0.0102 0.0029 1.0000
9.500 1.0815 0.01753 0.01233 -0.0095 0.0027 1.0000
9.750 1.1032 0.01822 0.01310 -0.0089 0.0026 1.0000
10.000 1.1240 0.01904 0.01401 -0.0082 0.0023 1.0000
10.250 1.1410 0.02041 0.01558 -0.0070 0.0021 1.0000
10.500 1.1569 0.02190 0.01728 -0.0058 0.0020 1.0000
10.750 1.1754 0.02292 0.01843 -0.0049 0.0019 1.0000
11.000 1.1920 0.02415 0.01983 -0.0038 0.0019 1.0000
11.250 1.2064 0.02559 0.02145 -0.0025 0.0018 1.0000
11.500 1.2186 0.02721 0.02327 -0.0011 0.0018 1.0000
11.750 1.2279 0.02903 0.02531 0.0006 0.0018 1.0000
12.000 1.2332 0.03102 0.02752 0.0027 0.0017 1.0000
12.250 1.2324 0.03319 0.02991 0.0053 0.0017 1.0000
12.500 1.2275 0.03571 0.03265 0.0077 0.0017 1.0000
12.750 1.2186 0.03876 0.03592 0.0095 0.0017 1.0000
13.000 1.2064 0.04244 0.03983 0.0104 0.0017 1.0000
13.250 1.1913 0.04686 0.04447 0.0102 0.0016 1.0000
13.500 1.1720 0.05237 0.05019 0.0086 0.0016 1.0000
13.750 1.1473 0.05957 0.05760 0.0050 0.0017 1.0000
14.000 1.1199 0.06866 0.06689 -0.0009 0.0017 1.0000
14.250 1.0818 0.08307 0.08150 -0.0113 0.0017 1.0000
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Polar data table (+)
Polar graphs
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