GIII BL86 AIRFOIL (modified line 31) (giiid-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL86 AIRFOIL (modified line 31) (giiid-il) Reynolds number: 100,000 Max Cl/Cd: 45.37 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiid-il-100000.txt Download as CSV file: xf-giiid-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5967 0.10014 0.09553 0.0000 1.0000 0.1129
-9.000 -0.6156 0.09471 0.09020 -0.0082 1.0000 0.1164
-8.750 -0.6418 0.08963 0.08512 -0.0151 1.0000 0.1171
-8.500 -0.6151 0.08529 0.08085 -0.0109 1.0000 0.1222
-8.250 -0.6200 0.08122 0.07679 -0.0127 1.0000 0.1265
-8.000 -0.6627 0.07793 0.07314 -0.0193 1.0000 0.1315
-7.750 -0.6328 0.07211 0.06760 -0.0167 1.0000 0.1357
-7.500 -0.6542 0.06970 0.06475 -0.0191 1.0000 0.1459
-7.250 -0.6306 0.06409 0.05942 -0.0177 1.0000 0.1494
-6.750 -0.6306 0.04597 0.03973 -0.0181 1.0000 0.0788
-6.500 -0.6191 0.04003 0.03288 -0.0150 1.0000 0.0632
-6.250 -0.6053 0.03613 0.02867 -0.0132 1.0000 0.0622
-6.000 -0.5909 0.03381 0.02579 -0.0107 1.0000 0.0636
-5.750 -0.5761 0.03071 0.02230 -0.0085 1.0000 0.0644
-5.500 -0.5589 0.02791 0.01918 -0.0065 1.0000 0.0650
-5.250 -0.5407 0.02573 0.01680 -0.0048 1.0000 0.0671
-5.000 -0.5225 0.02428 0.01522 -0.0030 1.0000 0.0714
-4.750 -0.5040 0.02314 0.01375 -0.0010 1.0000 0.0773
-4.500 -0.4840 0.02142 0.01212 0.0003 1.0000 0.0836
-4.250 -0.4643 0.02014 0.01079 0.0019 1.0000 0.0934
-4.000 -0.4463 0.01912 0.00987 0.0035 1.0000 0.1102
-3.750 -0.4286 0.01799 0.00886 0.0052 1.0000 0.1376
-3.500 -0.4121 0.01678 0.00800 0.0070 1.0000 0.1915
-3.250 -0.3966 0.01534 0.00729 0.0086 1.0000 0.2971
-3.000 -0.3901 0.01334 0.00764 0.0145 1.0000 0.7678
-2.750 -0.3678 0.01409 0.00844 0.0190 1.0000 0.8882
-2.500 -0.2381 0.01567 0.00938 0.0043 1.0000 0.9569
-2.250 -0.1135 0.01567 0.00887 -0.0131 1.0000 0.9827
-2.000 -0.0191 0.01503 0.00795 -0.0262 1.0000 1.0000
-1.750 -0.0203 0.01511 0.00798 -0.0227 1.0000 1.0000
-1.500 -0.0284 0.01526 0.00810 -0.0181 1.0000 1.0000
-1.250 -0.0375 0.01539 0.00820 -0.0133 1.0000 1.0000
-1.000 -0.0457 0.01550 0.00827 -0.0087 1.0000 1.0000
-0.750 -0.0261 0.01560 0.00830 -0.0089 0.9958 1.0000
-0.500 0.0206 0.01570 0.00831 -0.0138 0.9869 1.0000
-0.250 0.0672 0.01580 0.00835 -0.0186 0.9783 1.0000
0.000 0.1159 0.01589 0.00839 -0.0237 0.9702 1.0000
0.250 0.1602 0.01597 0.00846 -0.0278 0.9606 1.0000
0.500 0.2158 0.01598 0.00848 -0.0340 0.9545 1.0000
0.750 0.2619 0.01596 0.00848 -0.0381 0.9427 1.0000
1.000 0.3160 0.01569 0.00827 -0.0429 0.9278 1.0000
1.250 0.3552 0.01549 0.00810 -0.0444 0.9098 1.0000
1.500 0.3812 0.01549 0.00814 -0.0438 0.8926 1.0000
1.750 0.4044 0.01554 0.00825 -0.0426 0.8765 1.0000
2.000 0.4256 0.01560 0.00835 -0.0409 0.8607 1.0000
2.250 0.4455 0.01566 0.00845 -0.0388 0.8449 1.0000
2.500 0.4648 0.01571 0.00855 -0.0367 0.8292 1.0000
2.750 0.4840 0.01572 0.00861 -0.0343 0.8135 1.0000
3.000 0.5027 0.01575 0.00873 -0.0321 0.7960 1.0000
3.250 0.5216 0.01573 0.00878 -0.0298 0.7778 1.0000
3.500 0.5411 0.01561 0.00872 -0.0274 0.7597 1.0000
3.750 0.5609 0.01543 0.00861 -0.0249 0.7404 1.0000
4.000 0.5806 0.01524 0.00853 -0.0225 0.7176 1.0000
4.250 0.6006 0.01500 0.00837 -0.0201 0.6917 1.0000
4.500 0.6208 0.01476 0.00817 -0.0176 0.6609 1.0000
4.750 0.6406 0.01460 0.00801 -0.0150 0.6198 1.0000
5.000 0.6590 0.01457 0.00783 -0.0122 0.5610 1.0000
5.250 0.6755 0.01489 0.00788 -0.0095 0.4826 1.0000
5.500 0.6910 0.01554 0.00811 -0.0071 0.4043 1.0000
5.750 0.7066 0.01638 0.00860 -0.0050 0.3419 1.0000
6.000 0.7222 0.01729 0.00925 -0.0031 0.2893 1.0000
6.250 0.7365 0.01825 0.00999 -0.0011 0.2248 1.0000
6.500 0.7447 0.02015 0.01121 0.0017 0.1307 1.0000
6.750 0.7569 0.02188 0.01258 0.0041 0.0975 1.0000
7.000 0.7733 0.02345 0.01409 0.0061 0.0829 1.0000
7.250 0.7926 0.02504 0.01565 0.0076 0.0743 1.0000
7.500 0.8136 0.02683 0.01753 0.0089 0.0670 1.0000
7.750 0.8354 0.02870 0.01941 0.0099 0.0618 1.0000
8.000 0.8591 0.03183 0.02265 0.0107 0.0591 1.0000
8.250 0.8787 0.03409 0.02538 0.0123 0.0569 1.0000
8.500 0.8954 0.03635 0.02806 0.0139 0.0533 1.0000
8.750 0.9101 0.03937 0.03148 0.0156 0.0521 1.0000
9.000 0.9194 0.04310 0.03575 0.0177 0.0523 1.0000
9.250 0.9223 0.04750 0.04073 0.0201 0.0534 1.0000
9.500 0.9203 0.05207 0.04577 0.0223 0.0547 1.0000
9.750 0.9147 0.05657 0.05065 0.0241 0.0556 1.0000
10.000 0.9052 0.06102 0.05540 0.0257 0.0564 1.0000
10.250 0.8925 0.06540 0.05999 0.0270 0.0572 1.0000
10.500 0.8772 0.06967 0.06440 0.0280 0.0580 1.0000
10.750 0.8643 0.07452 0.06934 0.0279 0.0588 1.0000
11.000 0.7857 0.08770 0.08288 0.0170 0.0682 1.0000
11.250 0.6957 0.07847 0.07382 0.0275 0.0624 1.0000
11.500 0.6308 0.09596 0.09130 0.0163 0.0684 1.0000
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Polar data table (+)
Polar graphs
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