GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 100,000 Max Cl/Cd: 44.49 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiic-il-100000.txt Download as CSV file: xf-giiic-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.6052 0.09388 0.08930 -0.0039 1.0000 0.1217
-8.750 -0.6363 0.08784 0.08333 -0.0137 1.0000 0.1253
-8.500 -0.6827 0.08481 0.08003 -0.0187 1.0000 0.1265
-8.250 -0.6324 0.07910 0.07463 -0.0138 1.0000 0.1315
-8.000 -0.6412 0.07502 0.07048 -0.0160 1.0000 0.1377
-7.750 -0.5789 0.06065 0.05634 -0.0218 1.0000 0.1535
-7.500 -0.6389 0.06675 0.06213 -0.0166 1.0000 0.1485
-7.250 -0.6431 0.06264 0.05786 -0.0171 1.0000 0.1576
-7.000 -0.6562 0.04648 0.04003 -0.0170 1.0000 0.0733
-6.750 -0.6407 0.04221 0.03561 -0.0157 1.0000 0.0677
-6.500 -0.6294 0.03841 0.03138 -0.0135 1.0000 0.0666
-6.250 -0.6161 0.03513 0.02766 -0.0113 1.0000 0.0667
-6.000 -0.6013 0.03187 0.02391 -0.0088 1.0000 0.0655
-5.750 -0.5847 0.02913 0.02072 -0.0065 1.0000 0.0653
-5.500 -0.5664 0.02692 0.01815 -0.0045 1.0000 0.0666
-5.250 -0.5481 0.02542 0.01628 -0.0023 1.0000 0.0707
-5.000 -0.5289 0.02354 0.01429 -0.0008 1.0000 0.0755
-4.750 -0.5090 0.02217 0.01282 0.0008 1.0000 0.0808
-4.500 -0.4893 0.02079 0.01140 0.0024 1.0000 0.0889
-4.250 -0.4713 0.01974 0.01039 0.0041 1.0000 0.1024
-4.000 -0.4537 0.01866 0.00942 0.0059 1.0000 0.1218
-3.750 -0.4375 0.01751 0.00852 0.0078 1.0000 0.1591
-3.500 -0.4228 0.01617 0.00769 0.0098 1.0000 0.2355
-3.250 -0.4130 0.01396 0.00701 0.0124 1.0000 0.4672
-3.000 -0.4009 0.01365 0.00802 0.0191 1.0000 0.8241
-2.750 -0.3650 0.01465 0.00889 0.0209 1.0000 0.9085
-2.500 -0.2267 0.01603 0.00962 0.0037 1.0000 0.9570
-2.250 -0.1206 0.01597 0.00915 -0.0106 1.0000 0.9781
-2.000 -0.0183 0.01532 0.00820 -0.0251 1.0000 0.9989
-1.750 -0.0096 0.01528 0.00811 -0.0233 1.0000 1.0000
-1.500 -0.0160 0.01541 0.00821 -0.0189 1.0000 1.0000
-1.250 -0.0252 0.01556 0.00833 -0.0141 1.0000 1.0000
-1.000 -0.0342 0.01569 0.00844 -0.0094 1.0000 1.0000
-0.750 -0.0333 0.01581 0.00851 -0.0064 0.9986 1.0000
-0.500 0.0162 0.01590 0.00852 -0.0118 0.9893 1.0000
-0.250 0.0661 0.01600 0.00855 -0.0173 0.9805 1.0000
0.000 0.1155 0.01606 0.00857 -0.0225 0.9712 1.0000
0.250 0.1633 0.01610 0.00861 -0.0273 0.9614 1.0000
0.500 0.2207 0.01607 0.00858 -0.0338 0.9545 1.0000
0.750 0.2730 0.01592 0.00848 -0.0388 0.9418 1.0000
1.000 0.3244 0.01562 0.00822 -0.0430 0.9253 1.0000
1.250 0.3560 0.01549 0.00812 -0.0432 0.9048 1.0000
1.500 0.3820 0.01542 0.00808 -0.0423 0.8868 1.0000
1.750 0.4042 0.01543 0.00814 -0.0407 0.8704 1.0000
2.000 0.4246 0.01546 0.00820 -0.0388 0.8543 1.0000
2.250 0.4433 0.01553 0.00832 -0.0367 0.8367 1.0000
2.500 0.4623 0.01557 0.00840 -0.0346 0.8196 1.0000
2.750 0.4815 0.01556 0.00846 -0.0323 0.8027 1.0000
3.000 0.5009 0.01550 0.00844 -0.0300 0.7857 1.0000
3.250 0.5204 0.01541 0.00841 -0.0277 0.7677 1.0000
3.500 0.5399 0.01532 0.00839 -0.0255 0.7470 1.0000
3.750 0.5602 0.01511 0.00822 -0.0231 0.7271 1.0000
4.000 0.5800 0.01495 0.00816 -0.0209 0.7017 1.0000
4.250 0.6002 0.01476 0.00802 -0.0185 0.6733 1.0000
4.500 0.6202 0.01462 0.00788 -0.0161 0.6375 1.0000
4.750 0.6396 0.01459 0.00779 -0.0136 0.5900 1.0000
5.000 0.6580 0.01479 0.00781 -0.0111 0.5283 1.0000
5.250 0.6751 0.01528 0.00800 -0.0087 0.4574 1.0000
5.500 0.6915 0.01594 0.00832 -0.0066 0.3934 1.0000
5.750 0.7077 0.01671 0.00876 -0.0046 0.3429 1.0000
6.000 0.7245 0.01750 0.00937 -0.0029 0.3018 1.0000
6.250 0.7408 0.01824 0.01001 -0.0012 0.2597 1.0000
6.500 0.7549 0.01906 0.01072 0.0008 0.2016 1.0000
6.750 0.7627 0.02094 0.01195 0.0038 0.1103 1.0000
7.000 0.7752 0.02264 0.01343 0.0063 0.0852 1.0000
7.250 0.7906 0.02424 0.01496 0.0084 0.0731 1.0000
7.500 0.8078 0.02601 0.01666 0.0101 0.0649 1.0000
7.750 0.8289 0.02778 0.01853 0.0115 0.0601 1.0000
8.000 0.8511 0.03015 0.02090 0.0124 0.0563 1.0000
8.250 0.8714 0.03256 0.02360 0.0137 0.0532 1.0000
8.500 0.8898 0.03480 0.02621 0.0152 0.0506 1.0000
8.750 0.9060 0.03772 0.02955 0.0169 0.0498 1.0000
9.000 0.9177 0.04105 0.03336 0.0189 0.0498 1.0000
9.250 0.9245 0.04485 0.03765 0.0211 0.0504 1.0000
9.500 0.9266 0.04899 0.04225 0.0233 0.0514 1.0000
9.750 0.9247 0.05325 0.04690 0.0253 0.0524 1.0000
10.000 0.9192 0.05753 0.05149 0.0272 0.0531 1.0000
10.250 0.9107 0.06186 0.05607 0.0287 0.0538 1.0000
10.500 0.8998 0.06628 0.06067 0.0300 0.0544 1.0000
10.750 0.8982 0.07194 0.06640 0.0304 0.0554 1.0000
11.000 0.8088 0.07991 0.07500 0.0251 0.0612 1.0000
11.250 0.7751 0.08994 0.08509 0.0174 0.0628 1.0000
11.500 0.7621 0.09782 0.09295 0.0133 0.0655 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL75 AIRFOIL (giiic-il)