GIII BL167 AIRFOIL (giiig-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL167 AIRFOIL (giiig-il) Reynolds number: 500,000 Max Cl/Cd: 78.82 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiig-il-500000.txt Download as CSV file: xf-giiig-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5875 0.11433 0.11207 0.0085 1.0000 0.0137
-10.000 -0.5852 0.11029 0.10804 0.0067 1.0000 0.0141
-9.750 -0.5833 0.10615 0.10392 0.0047 1.0000 0.0144
-5.500 -0.5005 0.02559 0.02107 -0.0171 0.9971 0.0180
-5.250 -0.4726 0.01949 0.01435 -0.0178 0.9935 0.0162
-5.000 -0.4399 0.01701 0.01147 -0.0187 0.9893 0.0168
-4.750 -0.4046 0.01571 0.00991 -0.0203 0.9858 0.0175
-4.500 -0.3716 0.01323 0.00719 -0.0216 0.9831 0.0198
-4.250 -0.3390 0.01239 0.00628 -0.0227 0.9770 0.0216
-4.000 -0.3054 0.01160 0.00542 -0.0240 0.9713 0.0236
-3.750 -0.2737 0.01102 0.00476 -0.0248 0.9635 0.0256
-3.500 -0.2440 0.01017 0.00385 -0.0253 0.9556 0.0307
-3.250 -0.2162 0.00984 0.00348 -0.0253 0.9449 0.0363
-3.000 -0.1900 0.00938 0.00300 -0.0249 0.9342 0.0476
-2.750 -0.1640 0.00909 0.00271 -0.0245 0.9240 0.0604
-2.500 -0.1383 0.00884 0.00243 -0.0240 0.9139 0.0749
-2.250 -0.1131 0.00854 0.00222 -0.0235 0.9034 0.1002
-2.000 -0.0895 0.00795 0.00201 -0.0229 0.8935 0.2056
-1.750 -0.0779 0.00607 0.00174 -0.0204 0.8834 0.6685
-1.500 -0.0550 0.00586 0.00175 -0.0191 0.8742 0.7550
-1.250 -0.0304 0.00578 0.00173 -0.0181 0.8657 0.7969
-1.000 -0.0056 0.00575 0.00172 -0.0171 0.8575 0.8276
-0.750 0.0196 0.00572 0.00171 -0.0163 0.8472 0.8494
-0.500 0.0442 0.00571 0.00171 -0.0153 0.8365 0.8723
-0.250 0.0691 0.00572 0.00170 -0.0143 0.8265 0.8905
0.000 0.0937 0.00575 0.00171 -0.0132 0.8165 0.9097
0.250 0.1170 0.00581 0.00180 -0.0116 0.8063 0.9338
0.500 0.1442 0.00587 0.00183 -0.0112 0.7976 0.9469
0.750 0.1727 0.00590 0.00183 -0.0113 0.7889 0.9555
1.000 0.2052 0.00594 0.00184 -0.0123 0.7799 0.9611
1.250 0.2355 0.00599 0.00186 -0.0128 0.7714 0.9690
1.500 0.2711 0.00602 0.00189 -0.0145 0.7620 0.9728
1.750 0.3061 0.00606 0.00192 -0.0162 0.7521 0.9777
2.000 0.3404 0.00610 0.00195 -0.0177 0.7422 0.9830
2.250 0.3777 0.00613 0.00196 -0.0198 0.7294 0.9861
2.500 0.4131 0.00616 0.00194 -0.0215 0.7006 0.9906
2.750 0.4482 0.00622 0.00195 -0.0232 0.6738 0.9950
3.000 0.4844 0.00632 0.00197 -0.0252 0.6385 0.9987
3.250 0.5123 0.00650 0.00200 -0.0254 0.5932 1.0000
3.500 0.5344 0.00681 0.00208 -0.0245 0.5184 1.0000
3.750 0.5533 0.00759 0.00230 -0.0233 0.3920 1.0000
4.000 0.5733 0.00825 0.00258 -0.0222 0.3025 1.0000
4.250 0.5920 0.00907 0.00292 -0.0210 0.1929 1.0000
4.500 0.6090 0.01013 0.00343 -0.0195 0.0803 1.0000
4.750 0.6292 0.01082 0.00395 -0.0183 0.0451 1.0000
5.000 0.6500 0.01146 0.00459 -0.0170 0.0343 1.0000
5.250 0.6727 0.01186 0.00505 -0.0161 0.0308 1.0000
5.500 0.6945 0.01241 0.00561 -0.0151 0.0266 1.0000
5.750 0.7135 0.01342 0.00672 -0.0136 0.0237 1.0000
6.000 0.7360 0.01400 0.00739 -0.0126 0.0222 1.0000
6.250 0.7579 0.01472 0.00818 -0.0116 0.0204 1.0000
6.500 0.7807 0.01531 0.00879 -0.0109 0.0183 1.0000
6.750 0.7973 0.01741 0.01101 -0.0092 0.0163 1.0000
7.000 0.8196 0.01855 0.01228 -0.0083 0.0155 1.0000
7.250 0.8424 0.01967 0.01354 -0.0074 0.0147 1.0000
7.500 0.8643 0.02128 0.01534 -0.0064 0.0140 1.0000
7.750 0.8855 0.02299 0.01727 -0.0054 0.0132 1.0000
8.000 0.9071 0.02384 0.01822 -0.0048 0.0122 1.0000
8.250 0.9275 0.02479 0.01926 -0.0041 0.0113 1.0000
8.500 0.9432 0.02756 0.02230 -0.0028 0.0109 1.0000
8.750 0.9533 0.03149 0.02665 -0.0008 0.0107 1.0000
9.000 0.9591 0.03570 0.03129 0.0014 0.0106 1.0000
9.250 0.9631 0.03961 0.03557 0.0035 0.0106 1.0000
9.500 0.9673 0.04302 0.03932 0.0056 0.0109 1.0000
15.250 0.5842 0.16152 0.15936 -0.0235 0.0159 1.0000
15.500 0.5852 0.16456 0.16241 -0.0249 0.0158 1.0000
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Polar data table (+)
Polar graphs
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