GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 1,000,000 Max Cl/Cd: 82.13 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiih-il-1000000.txt Download as CSV file: xf-giiih-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.5949 0.03820 0.03571 -0.0254 1.0000 0.0094
-6.750 -0.6215 0.02275 0.01920 -0.0176 1.0000 0.0091
-6.500 -0.5953 0.01927 0.01524 -0.0179 0.9974 0.0096
-6.250 -0.5675 0.01541 0.01079 -0.0187 0.9945 0.0102
-6.000 -0.5378 0.01367 0.00883 -0.0195 0.9909 0.0109
-5.750 -0.5053 0.01293 0.00800 -0.0208 0.9873 0.0115
-5.500 -0.4720 0.01228 0.00728 -0.0222 0.9836 0.0122
-5.250 -0.4411 0.01184 0.00678 -0.0230 0.9767 0.0132
-5.000 -0.4091 0.01134 0.00621 -0.0240 0.9700 0.0140
-4.750 -0.3802 0.01096 0.00576 -0.0242 0.9597 0.0144
-4.500 -0.3567 0.00958 0.00420 -0.0234 0.9473 0.0155
-4.250 -0.3314 0.00912 0.00368 -0.0229 0.9347 0.0168
-4.000 -0.3057 0.00889 0.00340 -0.0224 0.9224 0.0182
-3.750 -0.2798 0.00870 0.00316 -0.0219 0.9108 0.0199
-3.500 -0.2536 0.00853 0.00293 -0.0216 0.8997 0.0208
-3.250 -0.2285 0.00804 0.00236 -0.0210 0.8887 0.0257
-3.000 -0.2016 0.00795 0.00224 -0.0208 0.8790 0.0292
-2.750 -0.1754 0.00770 0.00196 -0.0204 0.8698 0.0360
-2.500 -0.1482 0.00763 0.00187 -0.0203 0.8606 0.0401
-2.250 -0.1215 0.00744 0.00164 -0.0201 0.8521 0.0467
-2.000 -0.0946 0.00734 0.00151 -0.0199 0.8430 0.0524
-1.750 -0.0678 0.00719 0.00136 -0.0197 0.8323 0.0634
-1.500 -0.0417 0.00693 0.00123 -0.0194 0.8209 0.1093
-1.250 -0.0185 0.00618 0.00106 -0.0189 0.8104 0.3075
-1.000 -0.0013 0.00482 0.00087 -0.0173 0.8008 0.6727
-0.750 0.0238 0.00463 0.00088 -0.0167 0.7919 0.7441
-0.500 0.0501 0.00457 0.00087 -0.0163 0.7833 0.7758
-0.250 0.0769 0.00453 0.00085 -0.0160 0.7740 0.7990
0.000 0.1033 0.00448 0.00086 -0.0156 0.7649 0.8224
0.250 0.1288 0.00443 0.00088 -0.0149 0.7562 0.8542
0.500 0.1549 0.00440 0.00090 -0.0144 0.7467 0.8757
0.750 0.1815 0.00439 0.00092 -0.0140 0.7371 0.8907
1.000 0.2077 0.00440 0.00094 -0.0135 0.7273 0.9076
1.250 0.2345 0.00442 0.00096 -0.0132 0.7167 0.9197
1.500 0.2617 0.00444 0.00099 -0.0130 0.7053 0.9306
1.750 0.2888 0.00448 0.00102 -0.0128 0.6928 0.9420
2.000 0.3159 0.00457 0.00105 -0.0125 0.6670 0.9530
2.250 0.3447 0.00469 0.00109 -0.0127 0.6366 0.9621
2.500 0.3739 0.00485 0.00115 -0.0131 0.6062 0.9709
2.750 0.4058 0.00502 0.00122 -0.0141 0.5721 0.9771
3.000 0.4361 0.00531 0.00131 -0.0148 0.5099 0.9836
3.250 0.4686 0.00585 0.00148 -0.0163 0.4168 0.9870
3.500 0.5009 0.00637 0.00169 -0.0177 0.3382 0.9908
3.750 0.5325 0.00687 0.00190 -0.0190 0.2629 0.9945
4.000 0.5649 0.00757 0.00218 -0.0207 0.1647 0.9971
4.500 0.6210 0.00862 0.00276 -0.0218 0.0617 1.0000
4.750 0.6432 0.00893 0.00300 -0.0208 0.0453 1.0000
5.000 0.6659 0.00923 0.00326 -0.0199 0.0355 1.0000
5.250 0.6884 0.00960 0.00361 -0.0190 0.0281 1.0000
5.500 0.7120 0.00985 0.00388 -0.0183 0.0251 1.0000
5.750 0.7339 0.01035 0.00441 -0.0172 0.0205 1.0000
6.000 0.7573 0.01068 0.00477 -0.0164 0.0192 1.0000
6.250 0.7812 0.01099 0.00511 -0.0158 0.0178 1.0000
6.500 0.8050 0.01134 0.00548 -0.0152 0.0163 1.0000
6.750 0.8269 0.01199 0.00617 -0.0143 0.0142 1.0000
7.000 0.8490 0.01266 0.00694 -0.0134 0.0132 1.0000
7.250 0.8733 0.01303 0.00736 -0.0129 0.0125 1.0000
7.500 0.8970 0.01350 0.00787 -0.0123 0.0116 1.0000
7.750 0.9206 0.01397 0.00838 -0.0118 0.0108 1.0000
8.000 0.9434 0.01457 0.00901 -0.0112 0.0101 1.0000
8.250 0.9583 0.01653 0.01118 -0.0093 0.0090 1.0000
8.500 0.9836 0.01673 0.01142 -0.0091 0.0087 1.0000
8.750 1.0071 0.01721 0.01197 -0.0086 0.0082 1.0000
9.000 1.0292 0.01794 0.01279 -0.0080 0.0077 1.0000
9.250 1.0511 0.01869 0.01362 -0.0073 0.0073 1.0000
9.500 1.0726 0.01943 0.01443 -0.0067 0.0069 1.0000
9.750 1.0933 0.02026 0.01534 -0.0060 0.0066 1.0000
10.000 1.1103 0.02171 0.01695 -0.0048 0.0063 1.0000
10.250 1.1119 0.02595 0.02167 -0.0019 0.0059 1.0000
10.500 1.1273 0.02739 0.02330 -0.0007 0.0058 1.0000
10.750 1.1426 0.02870 0.02478 0.0004 0.0057 1.0000
11.000 1.1541 0.03042 0.02670 0.0019 0.0055 1.0000
11.250 1.1607 0.03257 0.02909 0.0038 0.0054 1.0000
11.500 1.1602 0.03509 0.03186 0.0063 0.0052 1.0000
11.750 1.1513 0.03796 0.03498 0.0092 0.0051 1.0000
12.000 1.1377 0.04139 0.03865 0.0113 0.0050 1.0000
12.250 1.1179 0.04591 0.04342 0.0121 0.0050 1.0000
12.500 1.0953 0.05146 0.04921 0.0111 0.0050 1.0000
12.750 1.0691 0.05854 0.05652 0.0077 0.0050 1.0000
13.000 1.0418 0.06735 0.06552 0.0018 0.0051 1.0000
13.250 1.0116 0.07940 0.07775 -0.0075 0.0052 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL207 AIRFOIL (giiih-il)