Remarkable Aerodynamic Performance of Triangle Cross Section Configuration for Fully RLV
- Paper number
IAC-10,D2,5,11,x8349
- Author
Prof. Shigeru Aso, Kyushu University, Japan
- Coauthor
Mr. Takuro Ishida, Kyushu University, Japan
- Coauthor
Dr. Yasuhiro Tani, Kyushu University, Japan
- Year
2010
- Abstract
For opening the next door with it, high lifts are required for them in terms of the aerodynamics, especially in subsonic region relating to the safe landing. In the previous study, it is reported the model with an isosceles right triangle cross sectional configuration for the fuselage shows high lift. However, more and more lift is required enough to be safer through low to high angle of attack of attacks. Based on the motivation above, the purposes of the present study are 1) to create a new configuration for higher lift and 2) to consider the applications for actual size one. A remarkable aerodynamic performance of triangle cross section have been achieved for FRLV(Fully Reusable Launch Vehicle). The key technology for the improvement of FRLV is to use vortex dynamics around fuselage and wing. A pair of leading-edge separation vortices, which are generated from both corner of bottom of triangle cross section, generate negative pressure on the upper surfaces of the triangle cross section of fuselage. The present authors have been investigate aerodynamic performance of wing-body configurations, whose cross section is circular, rectangular, square or triangle. Various aerodynamic shapes of wing-body configuration has been tested and evaluated. The results show that the fuselage with the triangle cross section with square corner have higher lift and lift-to-drag ratio is also high. A new configuration has been proposed and triangle edge for cross sectional configuration and the airfoil shape for the centerline profile. The results show the new model has about 1.5 larger lift coefficient compared to the conventional triangle model at 30deg angle of attack in subsonic. In addition, the lift is positive even if angle of attack is 0deg and pitching down moment at 0deg angle of attack is alleviated. It can be said this is the configuration having both benefits of a triangle and an airfoil. As for the second purpose, after the weight is estimation with HASA, the equations of motion are solved by an iterative calculation and the flight trajectory is compared to Space shuttles. The results say that the low heat fluxes in hypersonic region and the landing speed at the final phase are achieved for the triangle model. As a conclusion, the new model with triangle cross sectional configuration has feasibility for a future reusable launch vehicle.
- Abstract document
- Manuscript document
IAC-10,D2,5,11,x8349.pdf (🔒 authorized access only).
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