Abstract This paper presents an experimental study of the influence of viscous flows on the aerodynamic behaviour of waveriders. This investigation was carried out in the MARHy facility, under supersonic and rarefied flow conditions. Three supersonic and low density flow conditions were tested operating at Mach 2 and 4 with free stream pressures of 8 Pa and 2.67 Pa giving slip regime flows. Knudsen numbers associated with these flow conditions and this test model are between 2.79 × 10-3 and 7.33 × 10-4. In terms of pressure, these conditions are similar at altitudes between 50 km and 80 km. The studied waverider has a geometry proposed in the literature and optimised for a Mach 10 flow and an altitude of 50 km. The purpose of this work is to experimentally analyse how viscous effects will affect the aerodynamic performances of the waverider in off-design conditions. This work is based on the analysis of the upper and lower shock wave angles obtained from glow discharge imaging technique for different angles of attack and the three operating conditions. Results showed that the evolution of shock wave angles are Mach number dependent, as predicted by the inviscid shock relations, but also strongly depends on the flow pressure. From these experimental results, fitting equations have been established to predict the variation of upper and lower shock angles with the flow density, Mach number as a function of the angle of attack in continuum and especially in slip regime. Shock wave angles behaviour are compared to measured Lift-to-Drag ratio. Comparison presents a similar behaviour with flows conditions and shows that viscous layers appearing at low densities have a great influence on aerodynamic forces.

    Highlights Experimental measurements in supersonic wind tunnel MARHy. Study of shock waves variation in slip regime for different Knudsen numbers. Study of several waverider angle of attack and for three supersonic rarefied flows. Equation relating shock angles with Mach number, density and angle of attack. Correlation between Lift-to-Drag ratio and shock wave angles.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Correlation between waverider shock waves and aerodynamic forces in supersonic rarefied flow, experimental investigation in the wind tunnel MARHy


    Contributors:

    Published in:

    Acta Astronautica ; 199 ; 86-102


    Publication date :

    2022-07-10


    Size :

    17 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





    Aerodynamic Study of Cone-Derived Waverider as Supersonic Transport

    Buyanbaatar, Nomin / Ishikawa, Yuhei / Yamazaki, Wataru | Springer Verlag | 2022



    Aerodynamic analysis of the aerospaceplane HyPlane in supersonic rarefied flow

    Zuppardi, Gennaro / Savino, Raffaele / Russo, Gennaro et al. | Elsevier | 2016


    Wind tunnel results for a Mach 14 waverider

    Gillum, Michael / Kammeyer, Mark / Burnett, David | AIAA | 1994