| Budget Amount *help |
¥19,800,000 (Direct Cost: ¥19,800,000)
Fiscal Year 1990: ¥4,000,000 (Direct Cost: ¥4,000,000)
Fiscal Year 1989: ¥5,100,000 (Direct Cost: ¥5,100,000)
Fiscal Year 1988: ¥10,700,000 (Direct Cost: ¥10,700,000)
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| Research Abstract |
(1) Four wind tunnel models for future HST were tested by using the hypersonic wind tunnel at National Aerospace Laboratory (M=7.1, Re=0 (10^5-10^6)). The fourth model provided a L/D higher than 5.5 which is a remarkable value for the HST configuration with volume coefficient 0.1.
(2) Fundamental researches at Department of Aeronautics, the University of Tokyo, successfully supported the development of HST configuration as described in (1), through the experimental investigations of wave drag, friction drag, shock-boundary layer interactions, wing-body interference, separation vortices, boundary-layer transition, and so forth (M=7, Re=0 (10^6) ).
(3) Validity and applicability of CFD are recognized.
(4) The importance of linked system between CFD and CAD is discussed for the future development of HST. (1), (2) and (3) should be used for the construction of useful system. The fundamental concept of the system had been proposed by the author and others.
(5) As for the further researches, promising technologies for HST involving aerothermodynamic control of hypersonic flow and the extended study to the related environmental problems are highly recommended.
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