D.G.A. 1182 (dga1182-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: D.G.A. 1182 (dga1182-il) Reynolds number: 200,000 Max Cl/Cd: 37.49 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dga1182-il-200000-n5.txt Download as CSV file: xf-dga1182-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: D.G.A. 1182
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6137 0.09705 0.09190 0.0044 0.1602 0.0188
-8.250 -0.6116 0.09208 0.08695 -0.0002 0.1602 0.0189
-8.000 -0.6118 0.08676 0.08163 -0.0060 0.1601 0.0189
-7.750 -0.6090 0.08178 0.07657 -0.0103 0.1600 0.0189
-7.500 -0.6045 0.07728 0.07196 -0.0132 0.1600 0.0190
-7.250 -0.5978 0.07293 0.06747 -0.0154 0.1599 0.0191
-7.000 -0.5891 0.06866 0.06305 -0.0169 0.1598 0.0191
-6.750 -0.5782 0.06443 0.05863 -0.0180 0.1597 0.0192
-6.500 -0.5656 0.06027 0.05426 -0.0188 0.1596 0.0192
-6.250 -0.5515 0.05623 0.04997 -0.0192 0.1596 0.0193
-5.750 -0.5317 0.04538 0.03880 -0.0203 0.1595 0.0155
-5.500 -0.5118 0.04079 0.03384 -0.0199 0.1594 0.0135
-5.250 -0.4901 0.03772 0.03042 -0.0196 0.1594 0.0148
-5.000 -0.4671 0.03447 0.02678 -0.0189 0.1593 0.0152
-4.750 -0.4431 0.03091 0.02277 -0.0180 0.1593 0.0138
-4.500 -0.4176 0.02768 0.01904 -0.0170 0.1593 0.0127
-4.250 -0.3912 0.02511 0.01600 -0.0160 0.1593 0.0121
-4.000 -0.3648 0.02313 0.01368 -0.0153 0.1594 0.0119
-3.750 -0.3384 0.02148 0.01177 -0.0147 0.1595 0.0121
-3.500 -0.3122 0.02010 0.01018 -0.0142 0.1597 0.0125
-3.250 -0.2861 0.01915 0.00910 -0.0138 0.1599 0.0142
-3.000 -0.2601 0.01822 0.00805 -0.0133 0.1601 0.0160
-2.750 -0.2343 0.01727 0.00700 -0.0127 0.1603 0.0168
-2.500 -0.2083 0.01654 0.00613 -0.0123 0.1605 0.0179
-2.250 -0.1820 0.01595 0.00541 -0.0121 0.1608 0.0206
-2.000 -0.1553 0.01552 0.00485 -0.0119 0.1610 0.0248
-1.750 -0.1280 0.01532 0.00448 -0.0117 0.1605 0.0306
-1.500 -0.1014 0.01469 0.00427 -0.0117 0.1594 0.1797
-1.250 -0.0748 0.01445 0.00437 -0.0118 0.1578 0.3458
-1.000 -0.0468 0.01518 0.00485 -0.0118 0.1560 0.3809
-0.750 -0.0196 0.01538 0.00490 -0.0117 0.1549 0.3853
-0.500 0.0075 0.01550 0.00491 -0.0117 0.1545 0.3881
-0.250 0.0342 0.01580 0.00505 -0.0116 0.1532 0.3908
0.000 0.0613 0.01598 0.00512 -0.0116 0.1516 0.3934
0.250 0.0887 0.01604 0.00511 -0.0115 0.1503 0.3947
0.500 0.1159 0.01616 0.00516 -0.0115 0.1493 0.3957
0.750 0.1430 0.01632 0.00524 -0.0115 0.1483 0.3966
1.000 0.1700 0.01647 0.00536 -0.0114 0.1470 0.3976
1.250 0.1967 0.01664 0.00550 -0.0114 0.1456 0.3989
1.500 0.2232 0.01701 0.00581 -0.0113 0.1436 0.4002
1.750 0.2503 0.01711 0.00595 -0.0113 0.1400 0.4014
2.000 0.2773 0.01725 0.00615 -0.0113 0.1344 0.4022
2.250 0.3044 0.01730 0.00627 -0.0113 0.1298 0.4030
2.500 0.3316 0.01733 0.00639 -0.0112 0.1256 0.4042
2.750 0.3588 0.01738 0.00653 -0.0112 0.1217 0.4054
3.000 0.3863 0.01725 0.00657 -0.0112 0.1158 0.4062
3.250 0.4138 0.01718 0.00670 -0.0110 0.1016 0.4069
3.500 0.4412 0.01712 0.00675 -0.0110 0.0923 0.4078
3.750 0.4696 0.01681 0.00649 -0.0112 0.0865 0.4089
4.000 0.4985 0.01651 0.00619 -0.0113 0.0795 0.4100
4.250 0.5247 0.01682 0.00657 -0.0111 0.0718 0.4108
4.500 0.5509 0.01713 0.00695 -0.0110 0.0655 0.4117
4.750 0.5768 0.01749 0.00746 -0.0107 0.0611 0.4128
5.000 0.6026 0.01788 0.00798 -0.0105 0.0580 0.4143
5.250 0.6283 0.01828 0.00848 -0.0103 0.0551 0.4160
5.500 0.6536 0.01878 0.00914 -0.0100 0.0527 0.4177
5.750 0.6789 0.01934 0.00987 -0.0097 0.0513 0.4190
6.000 0.7040 0.01998 0.01069 -0.0093 0.0497 0.4200
6.250 0.7292 0.02060 0.01149 -0.0090 0.0476 0.4207
6.500 0.7547 0.02077 0.01173 -0.0089 0.0428 0.4214
6.750 0.7800 0.02114 0.01226 -0.0088 0.0371 0.4222
7.000 0.8044 0.02164 0.01287 -0.0086 0.0311 0.4230
7.250 0.8301 0.02214 0.01362 -0.0084 0.0235 0.4239
7.500 0.8543 0.02301 0.01459 -0.0080 0.0172 0.4248
7.750 0.8782 0.02397 0.01564 -0.0077 0.0130 0.4258
8.000 0.8981 0.02611 0.01811 -0.0067 0.0108 0.4269
8.250 0.9184 0.02833 0.02077 -0.0058 0.0100 0.4280
8.500 0.9368 0.03107 0.02398 -0.0049 0.0093 0.4292
8.750 0.9551 0.03352 0.02681 -0.0041 0.0083 0.4306
9.000 0.9732 0.03543 0.02897 -0.0036 0.0075 0.4321
9.250 0.9832 0.03932 0.03334 -0.0025 0.0070 0.4333
9.500 0.9829 0.04519 0.03982 -0.0011 0.0069 0.4341
10.000 0.9577 0.05897 0.05454 0.0004 0.0069 0.4346
10.250 0.9337 0.06566 0.06149 0.0001 0.0070 0.4345
|
Polar data table (+)
Polar graphs
<< Back to D.G.A. 1182 (dga1182-il)