GIII BL86 AIRFOIL (modified line 31) (giiid-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL86 AIRFOIL (modified line 31) (giiid-il) Reynolds number: 50,000 Max Cl/Cd: 30.97 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiid-il-50000.txt Download as CSV file: xf-giiid-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL86 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5775 0.11812 0.11147 0.0155 1.0000 0.2497
-9.500 -0.5896 0.11541 0.10887 0.0136 1.0000 0.2600
-9.250 -0.5919 0.11229 0.10580 0.0130 1.0000 0.2729
-9.000 -0.5845 0.10819 0.10168 0.0135 1.0000 0.2867
-8.750 -0.5831 0.10455 0.09810 0.0135 1.0000 0.3011
-8.500 -0.5888 0.10136 0.09499 0.0132 1.0000 0.3160
-8.250 -0.5576 0.09626 0.08982 0.0161 1.0000 0.3379
-8.000 -0.5775 0.09418 0.08788 0.0158 1.0000 0.3589
-7.750 -0.5453 0.08962 0.08326 0.0194 1.0000 0.3922
-6.750 -0.6298 0.05554 0.04777 -0.0185 1.0000 0.1314
-6.500 -0.6135 0.05078 0.04298 -0.0177 1.0000 0.1263
-6.250 -0.6025 0.04670 0.03848 -0.0163 1.0000 0.1236
-6.000 -0.5894 0.04323 0.03458 -0.0147 1.0000 0.1241
-5.750 -0.5746 0.03988 0.03071 -0.0128 1.0000 0.1240
-5.500 -0.5576 0.03671 0.02706 -0.0109 1.0000 0.1239
-5.250 -0.5387 0.03396 0.02387 -0.0090 1.0000 0.1264
-5.000 -0.5198 0.03168 0.02124 -0.0073 1.0000 0.1350
-4.750 -0.4987 0.02969 0.01885 -0.0056 1.0000 0.1450
-4.500 -0.4754 0.02761 0.01663 -0.0043 1.0000 0.1593
-4.250 -0.4515 0.02571 0.01485 -0.0032 1.0000 0.1854
-4.000 -0.4251 0.02377 0.01304 -0.0023 1.0000 0.2307
-3.750 -0.1534 0.02128 0.01226 -0.0289 1.0000 1.0000
-3.500 -0.1341 0.02074 0.01147 -0.0289 1.0000 1.0000
-3.250 -0.1149 0.02029 0.01079 -0.0287 1.0000 1.0000
-3.000 -0.0960 0.01990 0.01019 -0.0284 1.0000 1.0000
-2.750 -0.0778 0.01957 0.00970 -0.0280 1.0000 1.0000
-2.500 -0.0610 0.01931 0.00931 -0.0272 1.0000 1.0000
-2.250 -0.0465 0.01911 0.00902 -0.0261 1.0000 1.0000
-2.000 -0.0360 0.01901 0.00884 -0.0243 1.0000 1.0000
-1.750 -0.0314 0.01900 0.00877 -0.0214 1.0000 1.0000
-1.500 -0.0312 0.01905 0.00875 -0.0178 1.0000 1.0000
-1.250 -0.0328 0.01914 0.00877 -0.0139 1.0000 1.0000
-1.000 -0.0348 0.01925 0.00881 -0.0099 1.0000 1.0000
-0.750 -0.0361 0.01935 0.00885 -0.0061 1.0000 1.0000
-0.500 -0.0360 0.01947 0.00890 -0.0025 1.0000 1.0000
-0.250 -0.0342 0.01961 0.00897 0.0008 1.0000 1.0000
0.000 -0.0303 0.01978 0.00906 0.0038 1.0000 1.0000
0.250 -0.0245 0.01999 0.00918 0.0064 1.0000 1.0000
0.500 -0.0165 0.02024 0.00936 0.0086 1.0000 1.0000
0.750 -0.0064 0.02054 0.00959 0.0103 1.0000 1.0000
1.000 0.0056 0.02090 0.00988 0.0118 1.0000 1.0000
1.250 0.0189 0.02130 0.01024 0.0129 1.0000 1.0000
1.500 0.0333 0.02176 0.01066 0.0137 1.0000 1.0000
1.750 0.0484 0.02226 0.01115 0.0144 1.0000 1.0000
2.000 0.0640 0.02282 0.01169 0.0149 1.0000 1.0000
2.250 0.0977 0.02371 0.01261 0.0119 0.9938 1.0000
2.500 0.1616 0.02495 0.01399 0.0032 0.9723 1.0000
2.750 0.2218 0.02603 0.01523 -0.0042 0.9502 1.0000
3.000 0.2852 0.02697 0.01637 -0.0117 0.9269 1.0000
3.250 0.3379 0.02766 0.01732 -0.0168 0.9017 1.0000
3.500 0.3973 0.02816 0.01813 -0.0224 0.8747 1.0000
3.750 0.4645 0.02829 0.01869 -0.0284 0.8454 1.0000
4.000 0.5235 0.02799 0.01878 -0.0317 0.8147 1.0000
4.250 0.5636 0.02761 0.01872 -0.0312 0.7818 1.0000
4.500 0.5968 0.02696 0.01839 -0.0290 0.7461 1.0000
4.750 0.6251 0.02610 0.01777 -0.0255 0.7072 1.0000
5.000 0.6513 0.02502 0.01687 -0.0213 0.6645 1.0000
5.250 0.6762 0.02395 0.01589 -0.0168 0.6170 1.0000
5.500 0.6967 0.02342 0.01528 -0.0124 0.5617 1.0000
5.750 0.7141 0.02325 0.01486 -0.0082 0.5004 1.0000
6.000 0.7277 0.02350 0.01480 -0.0042 0.4338 1.0000
6.250 0.7390 0.02435 0.01518 -0.0005 0.3630 1.0000
6.500 0.7479 0.02623 0.01645 0.0030 0.2798 1.0000
6.750 0.7585 0.02867 0.01829 0.0061 0.2048 1.0000
7.000 0.7764 0.03087 0.02023 0.0080 0.1639 1.0000
7.250 0.7987 0.03318 0.02263 0.0094 0.1413 1.0000
7.500 0.8206 0.03554 0.02503 0.0106 0.1263 1.0000
7.750 0.8402 0.03822 0.02805 0.0121 0.1161 1.0000
8.000 0.8620 0.04158 0.03146 0.0130 0.1106 1.0000
8.250 0.8744 0.04520 0.03579 0.0150 0.1082 1.0000
8.500 0.8826 0.04888 0.04003 0.0169 0.1050 1.0000
8.750 0.8914 0.05227 0.04374 0.0185 0.1012 1.0000
9.000 0.8965 0.05634 0.04815 0.0200 0.1000 1.0000
9.250 0.8855 0.06154 0.05394 0.0217 0.1021 1.0000
9.500 0.8701 0.06684 0.05962 0.0227 0.1044 1.0000
9.750 0.8533 0.07202 0.06503 0.0230 0.1065 1.0000
10.000 0.8373 0.07699 0.07011 0.0231 0.1084 1.0000
10.250 0.8303 0.08210 0.07526 0.0228 0.1101 1.0000
10.500 0.6613 0.08485 0.07834 0.0218 0.1259 1.0000
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Polar data table (+)
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