Abstract
An experimental study on examining aerodynamic characteristics of fuselage cross sections for RLVs (Reusable Launch Vehicles) was conducted at Mach number 0.3, 0.9 and 4.0 in the wind tunnel of ISAS (Institute of Space and Astronautical Science), JAXA (Japan Aerospace Exploration Agency). Three bodies, having the same projected area and length, with and without a set of fins, were tested. Their cross sections are a circle, a square and a triangle with rounded corners. The results showed that the fuselage cross sections had large effects on aerodynamic characteristics in subsonic and transonic flow. The lift coefficient of the model having the triangular cross section with a set of the fins was larger than that of the others in high angles of attack region due to contributions of the separation vortices generated from the fuselage expanding to the wing surface.
Highlights
Space transportation system is one of the most important infrastructures for space activities
The lift coefficient of the model having the triangular cross section with a set of the fins was larger than that of the others in high angles of attack region due to contributions of the separation vortices generated from the fuselage expanding to the wing surface
An experimental study on examining aerodynamic characteristics of fuselage cross sections for RLVs was conducted at Mach number 0.3, 0.9 and 4.0 in the wind tunnel of ISAS, JAXA
Summary
Space transportation system is one of the most important infrastructures for space activities. High lift performance at low speed regime makes possible a shorter landing distance, and high lift-to-drag ratio performance allows easy approach during landing process, larger down and cross range in high speed region. Such RLVs have larger aerodynamic effects on a fuselage configuration due to a larg-. Investigating a favorable fuselage configuration of the RLVs is important to enhance the aerodynamic performances. While many useful studies have been carried out, very few studies have empirically investigated the aerodynamic effects on the fuselage cross sections for RLVs from low speed to supersonic region, including the changes of angle of attack.
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