GIII BL145 AIRFOIL (giiif-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL145 AIRFOIL (giiif-il) Reynolds number: 500,000 Max Cl/Cd: 62.27 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiif-il-500000-n5.txt Download as CSV file: xf-giiif-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6010 0.09386 0.09167 -0.0007 1.0000 0.0048
-9.250 -0.6042 0.08869 0.08653 -0.0039 1.0000 0.0047
-9.000 -0.6086 0.08316 0.08103 -0.0079 1.0000 0.0047
-8.750 -0.6160 0.07689 0.07479 -0.0146 1.0000 0.0046
-8.500 -0.6236 0.07102 0.06888 -0.0195 1.0000 0.0046
-8.250 -0.6270 0.06488 0.06265 -0.0230 1.0000 0.0046
-8.000 -0.6284 0.05846 0.05611 -0.0254 1.0000 0.0046
-7.750 -0.6288 0.05131 0.04875 -0.0266 1.0000 0.0046
-7.500 -0.6331 0.04163 0.03872 -0.0261 1.0000 0.0046
-7.250 -0.6549 0.02404 0.01980 -0.0209 1.0000 0.0047
-7.000 -0.6435 0.02029 0.01547 -0.0185 1.0000 0.0050
-6.750 -0.6170 0.01855 0.01345 -0.0189 0.9959 0.0053
-6.500 -0.5867 0.01751 0.01221 -0.0200 0.9900 0.0057
-6.250 -0.5561 0.01645 0.01097 -0.0210 0.9835 0.0062
-6.000 -0.5249 0.01568 0.01005 -0.0221 0.9766 0.0070
-5.750 -0.4945 0.01490 0.00910 -0.0228 0.9680 0.0078
-5.500 -0.4645 0.01403 0.00806 -0.0234 0.9584 0.0082
-5.250 -0.4373 0.01255 0.00639 -0.0235 0.9472 0.0095
-5.000 -0.4092 0.01201 0.00578 -0.0237 0.9353 0.0105
-4.750 -0.3823 0.01157 0.00523 -0.0235 0.9230 0.0119
-4.500 -0.3560 0.01128 0.00484 -0.0233 0.9104 0.0133
-4.000 -0.3060 0.01027 0.00361 -0.0221 0.8857 0.0168
-3.750 -0.2802 0.00998 0.00327 -0.0217 0.8749 0.0199
-3.500 -0.2540 0.00974 0.00292 -0.0214 0.8651 0.0229
-3.250 -0.2282 0.00945 0.00261 -0.0210 0.8557 0.0314
-3.000 -0.2018 0.00924 0.00239 -0.0207 0.8462 0.0419
-2.750 -0.1753 0.00906 0.00220 -0.0205 0.8377 0.0527
-2.500 -0.1487 0.00890 0.00205 -0.0203 0.8297 0.0665
-2.250 -0.1220 0.00874 0.00189 -0.0202 0.8220 0.0833
-1.750 -0.0686 0.00839 0.00161 -0.0199 0.8071 0.1269
-1.500 -0.0425 0.00815 0.00149 -0.0198 0.8003 0.1761
-1.250 -0.0181 0.00753 0.00132 -0.0195 0.7933 0.3243
-0.750 0.0236 0.00606 0.00117 -0.0171 0.7774 0.7314
-0.500 0.0492 0.00598 0.00116 -0.0165 0.7669 0.7689
-0.250 0.0750 0.00594 0.00115 -0.0160 0.7564 0.7970
0.000 0.1014 0.00591 0.00114 -0.0155 0.7464 0.8169
0.250 0.1274 0.00588 0.00116 -0.0150 0.7364 0.8406
0.500 0.1531 0.00585 0.00118 -0.0144 0.7266 0.8642
0.750 0.1792 0.00586 0.00120 -0.0139 0.7159 0.8831
1.000 0.2063 0.00587 0.00122 -0.0136 0.7051 0.8934
1.250 0.2338 0.00589 0.00124 -0.0135 0.6949 0.9023
1.500 0.2612 0.00593 0.00127 -0.0134 0.6842 0.9121
1.750 0.2890 0.00597 0.00132 -0.0134 0.6729 0.9216
2.000 0.3173 0.00602 0.00137 -0.0134 0.6607 0.9310
2.500 0.3753 0.00619 0.00151 -0.0140 0.6264 0.9497
2.750 0.4035 0.00648 0.00156 -0.0142 0.5613 0.9580
3.000 0.4298 0.00711 0.00170 -0.0142 0.4354 0.9670
3.250 0.4591 0.00757 0.00192 -0.0150 0.3723 0.9745
3.500 0.4890 0.00815 0.00219 -0.0160 0.2904 0.9808
3.750 0.5176 0.00888 0.00250 -0.0169 0.1898 0.9874
4.000 0.5474 0.00963 0.00286 -0.0180 0.1026 0.9928
4.250 0.5788 0.01012 0.00319 -0.0193 0.0630 0.9972
4.500 0.6075 0.01053 0.00351 -0.0199 0.0420 1.0000
4.750 0.6300 0.01088 0.00384 -0.0190 0.0310 1.0000
5.000 0.6532 0.01116 0.00416 -0.0182 0.0265 1.0000
5.250 0.6758 0.01156 0.00456 -0.0174 0.0218 1.0000
5.500 0.6985 0.01199 0.00504 -0.0165 0.0192 1.0000
5.750 0.7221 0.01232 0.00543 -0.0159 0.0172 1.0000
6.000 0.7454 0.01274 0.00590 -0.0152 0.0154 1.0000
6.250 0.7682 0.01325 0.00646 -0.0144 0.0133 1.0000
6.500 0.7897 0.01398 0.00727 -0.0135 0.0114 1.0000
6.750 0.8130 0.01445 0.00781 -0.0129 0.0105 1.0000
7.000 0.8358 0.01503 0.00847 -0.0122 0.0094 1.0000
7.250 0.8586 0.01562 0.00912 -0.0115 0.0085 1.0000
7.500 0.8808 0.01629 0.00984 -0.0108 0.0076 1.0000
7.750 0.9004 0.01744 0.01111 -0.0097 0.0067 1.0000
8.000 0.9234 0.01801 0.01181 -0.0092 0.0061 1.0000
8.250 0.9447 0.01890 0.01283 -0.0084 0.0056 1.0000
8.500 0.9656 0.01986 0.01392 -0.0076 0.0052 1.0000
8.750 0.9864 0.02078 0.01497 -0.0068 0.0048 1.0000
9.000 1.0070 0.02170 0.01600 -0.0060 0.0045 1.0000
9.250 1.0258 0.02290 0.01734 -0.0051 0.0042 1.0000
9.500 1.0371 0.02560 0.02037 -0.0033 0.0039 1.0000
9.750 1.0518 0.02755 0.02262 -0.0019 0.0038 1.0000
10.000 1.0624 0.03008 0.02550 -0.0002 0.0037 1.0000
10.250 1.0670 0.03335 0.02918 0.0020 0.0036 1.0000
10.500 1.0632 0.03744 0.03372 0.0046 0.0035 1.0000
10.750 1.0489 0.04194 0.03863 0.0078 0.0035 1.0000
11.000 1.0268 0.04668 0.04371 0.0105 0.0035 1.0000
11.250 1.0021 0.05210 0.04941 0.0110 0.0035 1.0000
11.500 0.9770 0.05839 0.05593 0.0092 0.0035 1.0000
11.750 0.9525 0.06586 0.06359 0.0049 0.0035 1.0000
12.000 0.9299 0.07501 0.07289 -0.0020 0.0036 1.0000
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Polar data table (+)
Polar graphs
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