Supersonic flow around space shuttle
The figure represents the flow around space shuttle with carrier rocket. Density gradient vector modulus and streamlines are shown.
Hypersonic flow around landing module
Pressure distribution for hypersonic landing module airflow (M=14) is shown.
Supersonic airflow around the body of rotation
The figure on the left presents the numerical simulation results for the
airflow with the Mach number 2 around a body with a needle (density
distribution is shown with the help of 256 shades of gray). The figure on
the right is a schlieren photograph of this process.
The comparison shows quite a satisfactory degree of conformity between
the computation results and the experimental data. Compression shocks layout,
their geometric configuration and strength are almost completely congruent.
Sources of energy and flow handling
Utility power of the flow may be supplied in a few different ways.
For example, laser emission focusing, stream injection, electric discharge, etc.
Utility power may considerably change the flow characteristics,
which in its turn can result in a considerable change of aerodynamic
characteristics of objects, such as resistance or lift force. This
feature of energy sources allows to potentially use them to control
the degree of the aircraft load and for flight control purposes.
Animation shows pressure distribution when the body is moving in a
supersonic flow in the presence of a periodic utility power source.
The pressure differences on the front face of the cylinder before and
after the process of utility power supplement are clearly seen. In this
case utility power source functions as a needle for pointed bodies and
considerably reduces the coefficient of resistance.
Steady airflow processes for rocket and missile parts
Rocket and missile propulsion on the exterior ballistics stage is
determined by the aerodynamic characteristics of these objects. Separation
effects, turbulence and many other physical phenomena make definition of
the aircraft aerodynamic characteristics one of the most difficult and
pressing of the modern problems.
The figures present simulation results for supersonic airflow around missile stabilizers.
As the stabilizers are characterised by a curved shape the problem has
been solved in a complete 3D statement in the setup mode.
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