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Aerodynamics of Reentry Space Vehicles

#3550


Testing Aerodynamics of Reentry Space Vehicles with Simulation of Real-Flight Viscous Effects

Tech Area / Field

  • PHY-NGD/Fluid Mechanics and Gas Dynamics/Physics
  • SAT-AER/Aeronautics/Space, Aircraft and Surface Transportation
  • SAT-VEC/Space Launch Vehicles and Support Equipment/Space, Aircraft and Surface Transportation

Status
8 Project completed

Registration date
26.06.2006

Completion date
09.12.2011

Senior Project Manager
Ryzhova T B

Leading Institute
Siberian Branch of RAS / Institute of Theoretical and Applied Mechanics (ITPMech), Russia, Novosibirsk reg., Novosibirsk

Collaborators

  • Rheinisch-Westfalische Technische Hochschule / Lehrstuhl für Strömungslehre und Aerodznamisches Institut Aachen, Germany, Aachen\nEuropean Space Agency / European Space and Technology Center, The Netherlands, Noordwijk\nEADS Space Transportation, France, Les Mureaux

Project summary

The goal of the present project is experimental research on determining aerodynamic characteristics of typical hypersonic flying vehicles (experimental reentry demonstrator ARES and reentry capsule EXPERT) in the ranges of Mach and Reynolds numbers corresponding to real flight conditions. The project is based on using the experience accumulated within the ISTC project No. 2109. In contrast to previous studies, this project will involve a new approach to providing a uniform distribution of flow velocities along the test section, which will allow obtaining more reliable results and demonstrating the advantages of the modification proposed. A detailed analysis of accuracy and reliability of the measurement methods used and results obtained will be performed.

The experiments are expected to give new results on stability and controllability of the flying vehicles under consideration in a wide range of flight velocities and angles of attack and sideslip. These results will be used for composing the program of in-flight experiments to be performed.

In addition, new measurement techniques will be tested experimentally, and new data will be obtained on the boundary-layer transition on the models examined with natural Reynolds numbers.

The results obtained will be used to develop methods of adequate numerical simulation of complicated external and internal high-velocity flow and for future design of promising aerospace planes; the benefit of these results will be a shorter and less expensive design procedure. The results obtained will be published in the form of scientific papers and reports and will be available for the scientific community.


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