A cooperative effort between Hughes Missile Systems Company, NASA Langley Research Center and AF Wright Laboratory was performed to evaluate the adequacy of simplified aerodynamic predictive methods for estimating the leeside separation of weapons from a hypersonic air vehicle. Aerodynamic test results were obtained at the NASA Mach 6 wind tunnel facility (Reference 1), where typical store-shaped test models were traversed in the 'shielding' influence of an inclined flat plate. These data largely verify that aerodynamic predictive methods, based on Newtonian impact 'line-of-sight' approximation methods, yield representative force and moment characteristics acting on stores during their leeside carriage and upward eject launch. Based on these predicted data, simulated leeside launch trajectories of advanced submunition weapons show that they can be safely separated from a carriage vehicle at hypersonic speeds.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Hypersonic viscous shock-layer flows including leeside separation

    GOGINENI, P. R. / LEWIS, C. H. / DENYSYK, B. | AIAA | 1980


    Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows

    Buck, Gregory / Pulsonetti, Maria / Weilmuenster, Kenneth | AIAA | 2005


    Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows

    Buck, Gregory M. / Pulsonetti, Maria V. / Weilmuenster, K. James | NTRS | 2005


    Downstream Effects on Orbiter Leeside Flow Separation for Hypersonic Flows

    G. M. Buck / M. V. Pulsonetti / K. J. Weilmuenster | NTIS | 2005


    Comparisons of hypersonic leeside flow results for a delta wing

    Shieh, T. / Li, C. / Manna, M. | AIAA | 1994