GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 500,000 Max Cl/Cd: 60.69 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiih-il-500000-n5.txt Download as CSV file: xf-giiih-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.6242 0.08235 0.08020 -0.0089 1.0000 0.0061
-9.000 -0.6340 0.07546 0.07333 -0.0166 1.0000 0.0061
-8.750 -0.6446 0.06889 0.06671 -0.0215 1.0000 0.0061
-8.500 -0.6521 0.06152 0.05921 -0.0250 1.0000 0.0062
-8.250 -0.6574 0.05428 0.05179 -0.0270 1.0000 0.0064
-8.000 -0.6520 0.04946 0.04679 -0.0275 1.0000 0.0066
-7.750 -0.6447 0.04458 0.04171 -0.0273 1.0000 0.0067
-7.500 -0.6404 0.03811 0.03489 -0.0261 1.0000 0.0070
-7.250 -0.6534 0.02496 0.02073 -0.0213 1.0000 0.0077
-7.000 -0.6419 0.02111 0.01633 -0.0188 1.0000 0.0083
-6.750 -0.6143 0.01869 0.01349 -0.0194 0.9955 0.0090
-6.500 -0.5845 0.01736 0.01188 -0.0202 0.9903 0.0095
-6.250 -0.5550 0.01582 0.01011 -0.0210 0.9848 0.0105
-6.000 -0.5240 0.01534 0.00957 -0.0221 0.9781 0.0113
-5.750 -0.4935 0.01456 0.00867 -0.0229 0.9710 0.0120
-5.500 -0.4629 0.01374 0.00769 -0.0237 0.9639 0.0128
-5.250 -0.4338 0.01303 0.00686 -0.0241 0.9545 0.0136
-5.000 -0.4045 0.01259 0.00633 -0.0245 0.9446 0.0144
-4.750 -0.3781 0.01170 0.00532 -0.0243 0.9337 0.0155
-4.500 -0.3518 0.01117 0.00472 -0.0241 0.9224 0.0166
-4.250 -0.3257 0.01081 0.00429 -0.0237 0.9113 0.0177
-4.000 -0.2999 0.01048 0.00388 -0.0233 0.9004 0.0191
-3.750 -0.2739 0.01020 0.00353 -0.0229 0.8900 0.0209
-3.500 -0.2481 0.00989 0.00315 -0.0225 0.8801 0.0235
-3.250 -0.2220 0.00963 0.00287 -0.0222 0.8705 0.0276
-3.000 -0.1955 0.00947 0.00264 -0.0219 0.8616 0.0312
-2.750 -0.1691 0.00926 0.00239 -0.0216 0.8530 0.0355
-2.500 -0.1424 0.00910 0.00221 -0.0214 0.8444 0.0407
-2.250 -0.1155 0.00899 0.00204 -0.0213 0.8367 0.0456
-2.000 -0.0888 0.00881 0.00187 -0.0211 0.8285 0.0548
-1.750 -0.0619 0.00867 0.00172 -0.0209 0.8211 0.0639
-1.500 -0.0352 0.00850 0.00159 -0.0207 0.8134 0.0846
-1.250 -0.0097 0.00811 0.00146 -0.0205 0.8050 0.1685
-1.000 0.0093 0.00679 0.00120 -0.0195 0.7944 0.5030
-0.750 0.0296 0.00615 0.00117 -0.0180 0.7815 0.6899
-0.500 0.0544 0.00602 0.00117 -0.0172 0.7690 0.7484
-0.250 0.0790 0.00590 0.00119 -0.0163 0.7585 0.7985
0.000 0.1040 0.00583 0.00122 -0.0155 0.7490 0.8353
0.250 0.1304 0.00582 0.00121 -0.0150 0.7388 0.8519
0.500 0.1563 0.00580 0.00123 -0.0144 0.7279 0.8733
0.750 0.1831 0.00581 0.00125 -0.0141 0.7171 0.8875
1.000 0.2104 0.00584 0.00125 -0.0139 0.7062 0.8968
1.250 0.2377 0.00587 0.00127 -0.0137 0.6947 0.9067
1.500 0.2653 0.00592 0.00131 -0.0136 0.6823 0.9163
1.750 0.2932 0.00597 0.00135 -0.0136 0.6687 0.9264
2.000 0.3214 0.00604 0.00139 -0.0136 0.6535 0.9367
2.250 0.3509 0.00613 0.00145 -0.0140 0.6331 0.9455
2.500 0.3792 0.00637 0.00150 -0.0141 0.5830 0.9545
2.750 0.4067 0.00674 0.00158 -0.0142 0.5015 0.9637
3.000 0.4357 0.00730 0.00176 -0.0149 0.4103 0.9709
3.250 0.4656 0.00772 0.00195 -0.0157 0.3520 0.9779
3.500 0.4956 0.00821 0.00218 -0.0167 0.2844 0.9843
3.750 0.5263 0.00874 0.00243 -0.0178 0.2152 0.9895
4.000 0.5559 0.00945 0.00276 -0.0189 0.1292 0.9949
4.250 0.5873 0.00999 0.00310 -0.0202 0.0821 0.9991
4.500 0.6121 0.01035 0.00337 -0.0199 0.0608 1.0000
4.750 0.6348 0.01068 0.00365 -0.0191 0.0471 1.0000
5.000 0.6580 0.01098 0.00393 -0.0183 0.0388 1.0000
5.250 0.6810 0.01134 0.00426 -0.0175 0.0319 1.0000
5.500 0.7047 0.01164 0.00462 -0.0169 0.0287 1.0000
5.750 0.7283 0.01200 0.00500 -0.0162 0.0254 1.0000
6.000 0.7510 0.01251 0.00552 -0.0154 0.0215 1.0000
6.250 0.7748 0.01288 0.00595 -0.0148 0.0202 1.0000
6.500 0.7985 0.01329 0.00642 -0.0142 0.0188 1.0000
6.750 0.8223 0.01369 0.00688 -0.0137 0.0170 1.0000
7.000 0.8457 0.01417 0.00738 -0.0131 0.0154 1.0000
7.250 0.8663 0.01508 0.00837 -0.0121 0.0137 1.0000
7.500 0.8901 0.01550 0.00888 -0.0116 0.0130 1.0000
7.750 0.9137 0.01596 0.00940 -0.0111 0.0119 1.0000
8.000 0.9372 0.01642 0.00992 -0.0107 0.0108 1.0000
8.250 0.9600 0.01699 0.01055 -0.0101 0.0099 1.0000
8.500 0.9791 0.01813 0.01178 -0.0090 0.0089 1.0000
8.750 1.0010 0.01884 0.01261 -0.0084 0.0085 1.0000
9.000 1.0220 0.01968 0.01359 -0.0076 0.0079 1.0000
9.250 1.0430 0.02049 0.01450 -0.0068 0.0073 1.0000
9.500 1.0647 0.02112 0.01522 -0.0062 0.0067 1.0000
9.750 1.0862 0.02172 0.01588 -0.0057 0.0062 1.0000
10.000 1.1027 0.02307 0.01734 -0.0046 0.0057 1.0000
10.250 1.1205 0.02424 0.01869 -0.0035 0.0055 1.0000
10.500 1.1365 0.02560 0.02029 -0.0023 0.0053 1.0000
10.750 1.1508 0.02713 0.02204 -0.0010 0.0050 1.0000
11.000 1.1631 0.02879 0.02393 0.0005 0.0048 1.0000
11.250 1.1732 0.03057 0.02594 0.0021 0.0046 1.0000
11.500 1.1805 0.03242 0.02801 0.0039 0.0044 1.0000
11.750 1.1834 0.03433 0.03013 0.0062 0.0043 1.0000
12.000 1.1836 0.03642 0.03243 0.0082 0.0042 1.0000
12.250 1.1814 0.03878 0.03498 0.0099 0.0041 1.0000
12.500 1.1768 0.04151 0.03792 0.0110 0.0040 1.0000
12.750 1.1682 0.04495 0.04157 0.0114 0.0040 1.0000
13.000 1.1573 0.04897 0.04580 0.0109 0.0039 1.0000
13.250 1.1414 0.05420 0.05124 0.0092 0.0039 1.0000
13.500 1.1219 0.06071 0.05797 0.0058 0.0039 1.0000
13.750 1.0901 0.07076 0.06829 -0.0007 0.0039 1.0000
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Polar data table (+)
Polar graphs
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