Study of aerodynamic uncertainty on thecomplex slender vehicle at high angle of attack
2016
The phenomenon of lateral aerodynamic uncertainty is discovered
in the wind tunnel test on the slender vehicle at high angle of attack.
To analyze the mechanism of the phenomenon, the numerical simulation
method with random pulsation added in the free stream is used, and
the aerodynamic uncertainty of the vehicle under the wind tunnel test
condition is reproduced by the simulation. The analysis of the flow
field leads us to a conclusion that the mechanism of aerodynamic uncertainty
is the asymmetry separation, which has a high sensitivity to the disturbance
of the flow around the missle. The uncertainty with respect to the
angle of attack for a “+” configuration of the main
wing is given and the difference of the uncertainty between the “+”
and “×” configurations are then analyzed. At last,
the action of pulling up through the high angle of attack and the
process of temporary atmospheric turbulence are simulated to study
the effect of the real flight environment rather than the wind tunnel
condition to the aerodynamic uncertainty. Based on these results,
it can be concluded that the uncertainty is not looked upon as quite
severe in real flight environment as that in the wind tunnel condition,
and the maneuverability of flight can be controlled.
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