GIII BL126 AIRFOIL (giiie-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GIII BL126 AIRFOIL (giiie-il) Reynolds number: 500,000 Max Cl/Cd: 76.75 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiie-il-500000.txt Download as CSV file: xf-giiie-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL126 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4816 0.09550 0.09344 -0.0068 1.0000 0.0177
-9.750 -0.6088 0.09724 0.09510 -0.0010 1.0000 0.0157
-9.500 -0.6150 0.09159 0.08948 -0.0041 1.0000 0.0161
-9.250 -0.6159 0.08726 0.08517 -0.0066 1.0000 0.0163
-9.000 -0.6192 0.08182 0.07976 -0.0113 1.0000 0.0164
-8.750 -0.6288 0.07527 0.07319 -0.0181 1.0000 0.0164
-8.500 -0.6335 0.07071 0.06858 -0.0204 1.0000 0.0166
-8.250 -0.6330 0.06649 0.06430 -0.0222 1.0000 0.0169
-8.000 -0.6297 0.06254 0.06027 -0.0234 1.0000 0.0173
-7.750 -0.6245 0.05848 0.05611 -0.0242 1.0000 0.0179
-7.500 -0.6176 0.05417 0.05167 -0.0248 1.0000 0.0188
-7.250 -0.6088 0.04950 0.04681 -0.0248 1.0000 0.0200
-7.000 -0.5864 0.04617 0.04314 -0.0240 1.0000 0.0225
-6.750 -0.5770 0.04222 0.03889 -0.0227 1.0000 0.0226
-6.500 -0.5867 0.03324 0.02942 -0.0201 1.0000 0.0239
-6.250 -0.5832 0.02520 0.02055 -0.0150 1.0000 0.0157
-6.000 -0.5651 0.02427 0.01948 -0.0132 0.9998 0.0154
-5.750 -0.5357 0.01907 0.01365 -0.0143 0.9942 0.0151
-5.500 -0.5029 0.01647 0.01066 -0.0155 0.9874 0.0158
-5.250 -0.4704 0.01416 0.00813 -0.0167 0.9799 0.0169
-5.000 -0.4358 0.01349 0.00743 -0.0185 0.9706 0.0190
-4.750 -0.4034 0.01267 0.00652 -0.0195 0.9588 0.0208
-4.500 -0.3732 0.01199 0.00571 -0.0200 0.9452 0.0222
-4.250 -0.3480 0.01100 0.00460 -0.0194 0.9301 0.0244
-4.000 -0.3230 0.01052 0.00407 -0.0188 0.9164 0.0286
-3.750 -0.2975 0.01019 0.00364 -0.0182 0.9044 0.0327
-3.500 -0.2735 0.00959 0.00306 -0.0174 0.8937 0.0495
-3.000 -0.2227 0.00901 0.00259 -0.0165 0.8752 0.1088
-2.750 -0.1968 0.00877 0.00241 -0.0162 0.8676 0.1376
-2.500 -0.1717 0.00841 0.00224 -0.0159 0.8599 0.1941
-2.250 -0.1500 0.00756 0.00198 -0.0152 0.8528 0.3618
-2.000 -0.1368 0.00620 0.00184 -0.0125 0.8451 0.7003
-1.750 -0.1130 0.00606 0.00187 -0.0114 0.8389 0.7679
-1.500 -0.0877 0.00602 0.00187 -0.0106 0.8324 0.8029
-1.250 -0.0620 0.00602 0.00186 -0.0099 0.8266 0.8279
-1.000 -0.0357 0.00601 0.00186 -0.0094 0.8201 0.8455
-0.750 -0.0099 0.00604 0.00187 -0.0087 0.8141 0.8633
-0.500 0.0162 0.00604 0.00188 -0.0081 0.8059 0.8781
-0.250 0.0419 0.00608 0.00188 -0.0074 0.7980 0.8926
0.000 0.0676 0.00609 0.00190 -0.0067 0.7896 0.9067
0.250 0.0932 0.00614 0.00194 -0.0059 0.7817 0.9208
0.500 0.1176 0.00622 0.00200 -0.0047 0.7734 0.9388
0.750 0.1459 0.00628 0.00207 -0.0044 0.7648 0.9503
1.000 0.1753 0.00633 0.00206 -0.0047 0.7578 0.9568
1.250 0.2080 0.00634 0.00209 -0.0057 0.7494 0.9615
1.500 0.2382 0.00638 0.00211 -0.0062 0.7419 0.9680
1.750 0.2729 0.00639 0.00213 -0.0078 0.7331 0.9716
2.000 0.3086 0.00641 0.00215 -0.0095 0.7238 0.9750
2.250 0.3433 0.00643 0.00217 -0.0111 0.7140 0.9791
2.500 0.3773 0.00645 0.00219 -0.0125 0.7016 0.9834
2.750 0.4140 0.00643 0.00217 -0.0145 0.6796 0.9862
3.000 0.4493 0.00648 0.00216 -0.0162 0.6517 0.9900
3.250 0.4833 0.00657 0.00221 -0.0176 0.6230 0.9942
3.500 0.5188 0.00676 0.00225 -0.0195 0.5762 0.9970
3.750 0.5519 0.00720 0.00234 -0.0211 0.4782 1.0000
4.000 0.5720 0.00796 0.00259 -0.0202 0.3612 1.0000
4.250 0.5928 0.00851 0.00287 -0.0193 0.2912 1.0000
4.500 0.6128 0.00910 0.00315 -0.0183 0.2176 1.0000
4.750 0.6304 0.00997 0.00355 -0.0169 0.1203 1.0000
5.000 0.6479 0.01083 0.00405 -0.0154 0.0553 1.0000
5.250 0.6678 0.01144 0.00460 -0.0140 0.0358 1.0000
5.500 0.6879 0.01207 0.00527 -0.0126 0.0289 1.0000
5.750 0.7095 0.01250 0.00573 -0.0116 0.0251 1.0000
6.000 0.7279 0.01336 0.00665 -0.0099 0.0219 1.0000
6.250 0.7463 0.01431 0.00769 -0.0083 0.0204 1.0000
6.500 0.7678 0.01490 0.00835 -0.0072 0.0189 1.0000
6.750 0.7898 0.01546 0.00896 -0.0063 0.0170 1.0000
7.000 0.8105 0.01628 0.00984 -0.0052 0.0157 1.0000
7.250 0.8277 0.01797 0.01161 -0.0036 0.0146 1.0000
7.500 0.8460 0.02022 0.01406 -0.0021 0.0139 1.0000
7.750 0.8679 0.02143 0.01542 -0.0012 0.0134 1.0000
8.000 0.8890 0.02296 0.01715 -0.0001 0.0128 1.0000
8.250 0.9097 0.02426 0.01863 0.0008 0.0120 1.0000
8.500 0.9293 0.02575 0.02030 0.0018 0.0113 1.0000
8.750 0.9461 0.02802 0.02286 0.0032 0.0110 1.0000
9.000 0.9598 0.03075 0.02591 0.0048 0.0108 1.0000
9.250 0.9630 0.03576 0.03149 0.0075 0.0111 1.0000
9.500 0.9467 0.04381 0.04021 0.0114 0.0125 1.0000
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Polar data table (+)
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