GIII BL86 AIRFOIL (modified line 31) (giiid-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL86 AIRFOIL (modified line 31) (giiid-il) Reynolds number: 500,000 Max Cl/Cd: 70.13 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiid-il-500000.txt Download as CSV file: xf-giiid-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.7391 0.03926 0.03600 -0.0185 1.0000 0.0130
-8.000 -0.7417 0.03317 0.02938 -0.0157 1.0000 0.0125
-7.750 -0.7355 0.02852 0.02421 -0.0132 1.0000 0.0125
-7.500 -0.7205 0.02582 0.02114 -0.0114 1.0000 0.0130
-7.250 -0.7008 0.02444 0.01949 -0.0101 1.0000 0.0137
-7.000 -0.6822 0.02287 0.01762 -0.0086 1.0000 0.0142
-6.750 -0.6698 0.01921 0.01354 -0.0062 1.0000 0.0147
-6.500 -0.6432 0.01738 0.01155 -0.0065 0.9954 0.0156
-6.250 -0.6088 0.01631 0.01039 -0.0083 0.9867 0.0167
-6.000 -0.5746 0.01537 0.00934 -0.0098 0.9769 0.0181
-5.750 -0.5402 0.01483 0.00871 -0.0114 0.9664 0.0198
-5.500 -0.5112 0.01345 0.00717 -0.0118 0.9542 0.0212
-5.250 -0.4857 0.01251 0.00614 -0.0114 0.9407 0.0233
-5.000 -0.4608 0.01204 0.00561 -0.0108 0.9284 0.0256
-4.750 -0.4357 0.01171 0.00520 -0.0102 0.9177 0.0282
-4.500 -0.4129 0.01101 0.00441 -0.0091 0.9083 0.0327
-4.250 -0.3881 0.01068 0.00401 -0.0084 0.8997 0.0389
-4.000 -0.3642 0.01014 0.00353 -0.0076 0.8918 0.0586
-3.750 -0.3400 0.00973 0.00325 -0.0070 0.8845 0.0954
-3.500 -0.3148 0.00942 0.00304 -0.0066 0.8773 0.1306
-3.250 -0.2900 0.00911 0.00285 -0.0061 0.8708 0.1714
-3.000 -0.2655 0.00871 0.00266 -0.0057 0.8641 0.2318
-2.750 -0.2429 0.00810 0.00244 -0.0049 0.8576 0.3381
-2.500 -0.2289 0.00682 0.00218 -0.0027 0.8509 0.6033
-2.250 -0.2083 0.00641 0.00216 -0.0010 0.8444 0.7155
-2.000 -0.1845 0.00628 0.00217 0.0002 0.8385 0.7736
-1.750 -0.1589 0.00624 0.00217 0.0009 0.8322 0.8055
-1.500 -0.1331 0.00625 0.00217 0.0017 0.8266 0.8293
-1.250 -0.1068 0.00623 0.00218 0.0022 0.8198 0.8481
-1.000 -0.0804 0.00625 0.00216 0.0028 0.8141 0.8637
-0.750 -0.0539 0.00626 0.00218 0.0033 0.8075 0.8777
-0.500 -0.0275 0.00629 0.00217 0.0039 0.8004 0.8902
-0.250 -0.0013 0.00629 0.00217 0.0045 0.7910 0.9024
0.000 0.0244 0.00632 0.00217 0.0054 0.7812 0.9149
0.250 0.0498 0.00637 0.00219 0.0063 0.7715 0.9276
0.500 0.0756 0.00646 0.00228 0.0073 0.7609 0.9413
0.750 0.1065 0.00655 0.00234 0.0070 0.7501 0.9492
1.000 0.1342 0.00657 0.00231 0.0072 0.7400 0.9554
1.250 0.1678 0.00660 0.00231 0.0060 0.7294 0.9584
1.500 0.2007 0.00663 0.00232 0.0049 0.7176 0.9621
1.750 0.2309 0.00666 0.00233 0.0044 0.7055 0.9673
2.000 0.2648 0.00669 0.00234 0.0031 0.6924 0.9703
2.250 0.3013 0.00674 0.00235 0.0012 0.6777 0.9723
2.500 0.3369 0.00680 0.00238 -0.0006 0.6617 0.9750
2.750 0.3704 0.00687 0.00241 -0.0019 0.6441 0.9785
3.000 0.4019 0.00695 0.00246 -0.0028 0.6242 0.9827
3.500 0.4736 0.00715 0.00258 -0.0065 0.5748 0.9872
3.750 0.5077 0.00733 0.00265 -0.0081 0.5384 0.9903
4.000 0.5393 0.00769 0.00276 -0.0093 0.4681 0.9937
4.250 0.5718 0.00837 0.00298 -0.0110 0.3563 0.9957
4.500 0.6048 0.00896 0.00325 -0.0127 0.2869 0.9980
4.750 0.6377 0.00938 0.00349 -0.0144 0.2424 1.0000
5.000 0.6601 0.00969 0.00370 -0.0137 0.2127 1.0000
5.250 0.6821 0.01001 0.00394 -0.0129 0.1843 1.0000
5.500 0.7031 0.01041 0.00420 -0.0120 0.1504 1.0000
5.750 0.7220 0.01106 0.00457 -0.0108 0.0936 1.0000
6.000 0.7384 0.01197 0.00519 -0.0091 0.0444 1.0000
6.250 0.7568 0.01259 0.00580 -0.0075 0.0336 1.0000
6.500 0.7753 0.01319 0.00642 -0.0059 0.0287 1.0000
6.750 0.7924 0.01393 0.00725 -0.0040 0.0257 1.0000
7.000 0.8120 0.01438 0.00776 -0.0026 0.0237 1.0000
7.250 0.8306 0.01498 0.00841 -0.0011 0.0219 1.0000
7.500 0.8482 0.01571 0.00918 0.0005 0.0201 1.0000
7.750 0.8604 0.01715 0.01073 0.0030 0.0182 1.0000
8.000 0.8807 0.01767 0.01133 0.0042 0.0173 1.0000
8.250 0.8996 0.01845 0.01220 0.0056 0.0161 1.0000
8.500 0.9185 0.01928 0.01310 0.0069 0.0150 1.0000
8.750 0.9374 0.02010 0.01396 0.0080 0.0139 1.0000
9.000 0.9483 0.02272 0.01673 0.0101 0.0125 1.0000
9.250 0.9695 0.02315 0.01728 0.0109 0.0118 1.0000
9.500 0.9873 0.02439 0.01867 0.0121 0.0111 1.0000
9.750 1.0041 0.02577 0.02021 0.0134 0.0105 1.0000
10.000 1.0200 0.02714 0.02174 0.0146 0.0100 1.0000
10.250 1.0345 0.02854 0.02328 0.0158 0.0096 1.0000
10.500 1.0470 0.03009 0.02496 0.0172 0.0092 1.0000
10.750 1.0537 0.03256 0.02762 0.0190 0.0089 1.0000
11.000 1.0501 0.03625 0.03163 0.0215 0.0087 1.0000
11.250 1.0386 0.03994 0.03564 0.0246 0.0086 1.0000
11.500 1.0256 0.04351 0.03947 0.0267 0.0086 1.0000
11.750 1.0126 0.04715 0.04335 0.0277 0.0085 1.0000
12.000 0.9986 0.05112 0.04754 0.0278 0.0086 1.0000
12.250 0.9851 0.05536 0.05198 0.0270 0.0086 1.0000
12.500 0.9717 0.06000 0.05680 0.0252 0.0086 1.0000
12.750 0.9582 0.06520 0.06216 0.0224 0.0086 1.0000
13.000 0.9444 0.07105 0.06817 0.0187 0.0087 1.0000
13.250 0.9293 0.07786 0.07513 0.0139 0.0087 1.0000
13.500 0.9128 0.08593 0.08336 0.0081 0.0088 1.0000
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Polar data table (+)
Polar graphs
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