This paper takes N-S equation as the basic control equation, selects turbulence model, and adopts the sliding mesh technology to conduct numerical simulation for the interference of missile jet flow and inflow on the flow field in different flow conditions. The results indicate that: the lift coefficient, drag coefficient and pressure center coefficient of missile body change with the changes of flowMach number and attack angle. The lift coefficient increases with the increase of Mach number in subsonic speed, decreases with the increase of Mach number in supersonic speed, and reaches a maximum value with the increase of Mach number in transonic speed. The change rule of drag coefficient and pressure center coefficient is the same as that of lift coefficient. That is, they increase with the increase of Mach number in subsonic speed, and decrease with the increase of Mach number in supersonic speed.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren




    Active Control of Aerodynamic Characteristics of Space Transportation System by Lateral Blowing

    Tadakuma, K. / Aso, S. / Tani, Y. et al. | British Library Conference Proceedings | 2004


    Active Control of Aerodynamic Characteristics of Next-Generation SST Wing by Lateral Blowing

    Kamishita, M. / Aso, S. / Karashima, K. et al. | British Library Conference Proceedings | 2000



    A Relationship between Lift and Lateral Aerodynamic Characteristics for Passenger Cars

    Howell, Jeff / Baden Fuller, Joshua | SAE Technical Papers | 2010