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Advances in Aircraft and Spacecraft Science
  Volume 8, Number 1, January 2021 , pages 53-67

Aerodynamics of a wing section along an entry path in Mars atmosphere
Gennaro Zuppardi and Giuseppe Mongelluzzo

    The increasing interest in the exploration of Mars stimulated the authors to study aerodynamic problems linked to space vehicles. The aim of this paper is to evaluate the aerodynamic effects of a flapped wing in collaborating with parachutes and retro-rockets to reduce velocity and with thrusters to control the spacecraft attitude. 3-D computations on a preliminary configuration of a blunt-cylinder, provided with flapped fins, quantified the beneficial influence of the fins. The present paper is focused on Aerodynamics of a wing section (NACA-0010) provided with a trailing edge flap. The influence of the flap deflection was evaluated by the increments of aerodynamic force and leading edge pitching moment coefficients with respect to the coefficients in clean configuration. The study was carried out by means of two Direct Simulation Monte Carlo (DSMC) codes (DS2V/3V solving 2-D/3-D flow fields, respectively). A DSMC code is indispensable to simulate complex flow fields on a wing generated by Shock Wave-Shock Wave Interaction (SWSWI) due to the flap deflection. The flap angle has to be a compromise between the aerodynamic effectiveness and the increases of aerodynamic load and heat flux on the wing section lower surface.
Key Words
    wing section Aerodynamics; hypersonic flow; direct simulation Monte Carlo method; wing-flap deflection; shock wave-shock wave interaction
Gennaro Zuppardi: Department of Industrial Engineering,
University of Naples "Federico II", Piazzale Tecchio 80, 80125, Naples, Italy

Giuseppe Mongelluzzo: INAF - Astronomical Observatory of Capodimonte, Salita Moiariello 16, 80131, Naples, Italy

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