GIII BL86 AIRFOIL (modified line 31) (giiid-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL86 AIRFOIL (modified line 31) (giiid-il) Reynolds number: 1,000,000 Max Cl/Cd: 75.18 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiid-il-1000000.txt Download as CSV file: xf-giiid-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.7726 0.03703 0.03535 -0.0298 1.0000 0.0056
-10.250 -0.8129 0.03116 0.02922 -0.0277 1.0000 0.0056
-10.000 -0.9005 0.03649 0.03402 -0.0187 1.0000 0.0054
-9.750 -0.9118 0.03043 0.02739 -0.0157 1.0000 0.0056
-9.500 -0.9041 0.02728 0.02386 -0.0138 1.0000 0.0058
-9.250 -0.8899 0.02514 0.02145 -0.0123 1.0000 0.0061
-9.000 -0.8716 0.02368 0.01977 -0.0113 1.0000 0.0062
-8.750 -0.8504 0.02275 0.01869 -0.0105 1.0000 0.0064
-8.500 -0.8416 0.01894 0.01438 -0.0080 1.0000 0.0067
-8.250 -0.8223 0.01747 0.01275 -0.0069 1.0000 0.0071
-8.000 -0.7998 0.01672 0.01191 -0.0062 1.0000 0.0074
-7.750 -0.7768 0.01608 0.01121 -0.0056 1.0000 0.0077
-7.500 -0.7501 0.01538 0.01042 -0.0057 0.9953 0.0082
-7.250 -0.7154 0.01463 0.00958 -0.0075 0.9761 0.0088
-7.000 -0.6816 0.01430 0.00917 -0.0090 0.9507 0.0094
-6.750 -0.6601 0.01314 0.00779 -0.0078 0.9225 0.0102
-6.500 -0.6376 0.01245 0.00696 -0.0069 0.9046 0.0110
-6.250 -0.6130 0.01207 0.00650 -0.0063 0.8925 0.0117
-6.000 -0.5881 0.01170 0.00603 -0.0058 0.8831 0.0126
-5.750 -0.5624 0.01134 0.00560 -0.0054 0.8750 0.0134
-5.500 -0.5361 0.01114 0.00534 -0.0051 0.8683 0.0140
-5.250 -0.5126 0.01032 0.00440 -0.0043 0.8616 0.0160
-5.000 -0.4867 0.01001 0.00403 -0.0040 0.8558 0.0175
-4.750 -0.4602 0.00973 0.00371 -0.0038 0.8502 0.0191
-4.500 -0.4334 0.00954 0.00348 -0.0036 0.8447 0.0203
-4.250 -0.4080 0.00910 0.00300 -0.0031 0.8396 0.0261
-4.000 -0.3815 0.00881 0.00269 -0.0028 0.8344 0.0342
-3.750 -0.3554 0.00852 0.00245 -0.0025 0.8294 0.0513
-3.500 -0.3292 0.00824 0.00227 -0.0023 0.8246 0.0768
-3.250 -0.3027 0.00797 0.00210 -0.0022 0.8193 0.1046
-3.000 -0.2764 0.00774 0.00195 -0.0020 0.8145 0.1347
-2.750 -0.2498 0.00749 0.00181 -0.0018 0.8096 0.1679
-2.500 -0.2238 0.00718 0.00168 -0.0016 0.8043 0.2193
-2.250 -0.1991 0.00675 0.00153 -0.0012 0.7992 0.3066
-2.000 -0.1789 0.00578 0.00128 -0.0001 0.7937 0.5064
-1.750 -0.1577 0.00516 0.00117 0.0011 0.7882 0.6590
-1.500 -0.1332 0.00493 0.00113 0.0019 0.7829 0.7236
-1.250 -0.1070 0.00480 0.00111 0.0023 0.7761 0.7595
-1.000 -0.0807 0.00473 0.00107 0.0028 0.7682 0.7885
-0.750 -0.0539 0.00468 0.00104 0.0031 0.7583 0.8097
-0.500 -0.0266 0.00465 0.00101 0.0033 0.7483 0.8253
-0.250 0.0005 0.00463 0.00099 0.0036 0.7389 0.8401
0.000 0.0276 0.00462 0.00097 0.0039 0.7281 0.8530
0.250 0.0548 0.00461 0.00096 0.0041 0.7160 0.8650
0.500 0.0819 0.00461 0.00097 0.0044 0.7045 0.8776
0.750 0.1089 0.00462 0.00099 0.0047 0.6930 0.8902
1.000 0.1350 0.00465 0.00103 0.0052 0.6807 0.9059
1.250 0.1612 0.00470 0.00107 0.0058 0.6680 0.9194
1.500 0.1882 0.00476 0.00109 0.0060 0.6541 0.9272
1.750 0.2159 0.00481 0.00113 0.0061 0.6391 0.9329
2.000 0.2427 0.00488 0.00116 0.0063 0.6236 0.9398
2.250 0.2708 0.00497 0.00121 0.0063 0.6059 0.9450
2.500 0.2979 0.00507 0.00127 0.0065 0.5880 0.9513
2.750 0.3257 0.00518 0.00134 0.0065 0.5680 0.9568
3.000 0.3547 0.00531 0.00142 0.0062 0.5480 0.9615
3.250 0.3820 0.00545 0.00151 0.0063 0.5247 0.9676
3.500 0.4124 0.00564 0.00162 0.0056 0.4925 0.9712
3.750 0.4425 0.00602 0.00176 0.0049 0.4255 0.9746
4.000 0.4702 0.00669 0.00200 0.0044 0.3239 0.9789
4.250 0.4989 0.00711 0.00221 0.0038 0.2730 0.9829
4.500 0.5328 0.00747 0.00242 0.0021 0.2324 0.9842
4.750 0.5668 0.00776 0.00260 0.0004 0.2047 0.9858
5.000 0.6001 0.00806 0.00280 -0.0011 0.1770 0.9877
5.250 0.6323 0.00841 0.00302 -0.0024 0.1447 0.9900
5.500 0.6629 0.00889 0.00332 -0.0035 0.1035 0.9927
5.750 0.6933 0.00958 0.00375 -0.0047 0.0532 0.9947
6.000 0.7257 0.01017 0.00418 -0.0062 0.0293 0.9962
6.250 0.7586 0.01057 0.00459 -0.0076 0.0228 0.9979
6.500 0.7906 0.01117 0.00524 -0.0089 0.0183 0.9995
6.750 0.8162 0.01144 0.00555 -0.0087 0.0173 1.0000
7.000 0.8362 0.01173 0.00587 -0.0074 0.0160 1.0000
7.250 0.8558 0.01210 0.00625 -0.0060 0.0147 1.0000
7.500 0.8731 0.01274 0.00695 -0.0042 0.0132 1.0000
7.750 0.8906 0.01337 0.00768 -0.0024 0.0124 1.0000
8.000 0.9119 0.01363 0.00797 -0.0014 0.0117 1.0000
8.250 0.9330 0.01397 0.00832 -0.0003 0.0108 1.0000
8.500 0.9537 0.01436 0.00873 0.0008 0.0099 1.0000
8.750 0.9705 0.01520 0.00962 0.0025 0.0089 1.0000
9.000 0.9873 0.01612 0.01065 0.0041 0.0083 1.0000
9.250 1.0088 0.01656 0.01115 0.0049 0.0078 1.0000
9.500 1.0296 0.01713 0.01180 0.0059 0.0072 1.0000
9.750 1.0503 0.01772 0.01243 0.0067 0.0068 1.0000
10.000 1.0711 0.01829 0.01304 0.0075 0.0064 1.0000
10.250 1.0888 0.01922 0.01404 0.0086 0.0059 1.0000
10.500 1.0954 0.02149 0.01653 0.0110 0.0055 1.0000
10.750 1.1147 0.02219 0.01732 0.0119 0.0053 1.0000
11.000 1.1314 0.02314 0.01839 0.0130 0.0051 1.0000
11.250 1.1456 0.02431 0.01969 0.0144 0.0049 1.0000
11.500 1.1572 0.02564 0.02116 0.0159 0.0047 1.0000
11.750 1.1654 0.02699 0.02266 0.0179 0.0046 1.0000
12.000 1.1726 0.02834 0.02414 0.0197 0.0044 1.0000
12.250 1.1790 0.02979 0.02571 0.0212 0.0043 1.0000
12.500 1.1847 0.03136 0.02739 0.0224 0.0042 1.0000
12.750 1.1903 0.03301 0.02915 0.0232 0.0041 1.0000
13.000 1.1940 0.03495 0.03120 0.0238 0.0040 1.0000
13.250 1.1954 0.03723 0.03360 0.0242 0.0039 1.0000
13.500 1.1929 0.04009 0.03660 0.0243 0.0038 1.0000
13.750 1.1870 0.04355 0.04021 0.0238 0.0038 1.0000
14.000 1.1774 0.04773 0.04456 0.0227 0.0037 1.0000
14.250 1.1649 0.05267 0.04967 0.0208 0.0037 1.0000
14.500 1.1498 0.05843 0.05561 0.0180 0.0037 1.0000
14.750 1.1324 0.06505 0.06240 0.0145 0.0037 1.0000
15.000 1.1123 0.07270 0.07022 0.0100 0.0038 1.0000
15.250 1.0873 0.08197 0.07967 0.0045 0.0038 1.0000
15.500 1.0528 0.09388 0.09178 -0.0023 0.0039 1.0000
15.750 0.7749 0.11534 0.11363 0.0012 0.0049 1.0000
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