III.3.2
Calculation of CAn
| A330 C601 | ||||||
| Ma ch CAa CAa, £orm f Ma ch CAa £ CAa | ||||||
|
0.2 |
5.4 | 4.61 | 1.17 | 0.208 | 4.44 | 5.19 |
|
0.4 |
5.6 | 4.80 | 1.17 | 0.416 | 4.62 | 5.4 |
|
0.6 |
6.1 | 5.18 | 1.18 | 0.624 | 5.0 | 5.89 |
|
0.8 |
7.3 | 5.92 | 1.23 | 0.832 | 5.74 | 7.06 |
| 0.85 | 7.95 | 6.22 | 1.28 | 0.884 | 6,04 | 7.73 |
|
0.9 |
7.0 | 6,59 | 1.06 | 0.936 | 6.42 | 6.8 |
10
Mach. number to drag increase
Influence of the different sweep
Mach drag
Mach drag
Curve for different lift coefficient
