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LABORATORY WORK №3
AIRCRAFT STABILITY AND CONTROL CHARACTERISTICS ESTIMATION
VIA DIGITAL DATCOM SOFTWARE
STANDARD TASK
Basing on the initial data of the aircraft body geometry and flight condition apply the Digital Datcom software to model its shape and obtain aerodynamic characteristics. Initial flight conditions and fuselage shape are given below:
Flight Condition:
|
Mach number |
0.90 |
1.40 |
2.5 |
|
Angle of attack in a ascending order |
-6.0 |
-4.0 |
-2.0 |
0.0 |
2.0 |
4.0 |
8.0 |
12.0 |
16.0 |
20.0 |
24.0 |
|
Reynolds number |
6.4E6 |
9.96E6 |
17.8E6 |
Body modelling is given on Fig. 1
Figure 1 Aircraft shape to be modelled
Aircraft geometry:
Wing area, Sw=8.85; MAC=2.46; wing span, b=4.28;
Aircraft centre of gravity location: X=4.14; Z=-0.20;
Body Information (Configuration)
|
X, Station (ft) |
R, (rad, ft) |
ZU (ft) |
ZL (ft) |
|
0.0 |
0.0 |
-0.595 |
-0.595 |
|
0.258 |
0.106 |
-0.476 |
-0.715 |
|
0.589 |
0.206 |
-0.372 |
-0.754 |
|
1.26 |
0.424 |
-0.138 |
-0.805 |
|
2.26 |
0.533 |
0.200 |
-0.868 |
|
2.59 |
0.533 |
0.334 |
-0.868 |
|
2.93 |
0.533 |
0.343 |
-0.868 |
|
3.59 |
0.533 |
0.343 |
-0.868 |
|
4.57 |
0.533 |
0.343 |
-0.868 |
|
6.26 |
0.533 |
0.343 |
-0.868 |
Conical type of nose; Sharp nosebody;
Length of body nose, lN = 2.59; Length of afterbody segment, lA = 3.67.