First Aerodynamics Division, National Aerospace Laboratory(NAL)
First Aerodynamics Division, National Aerospace Laboratory(NAL)
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory(NAL)
雑誌名
航空宇宙技術研究所報告
雑誌名(英)
Technical Report of National Aerospace Laboratory TR-542
巻
542
ページ
19
発行年
1978-09
抄録（英）
The aerodynamic damping derivatives on blunted cones and the AGARD HB-1, HB-2 models have been measured by use of an automatic free oscillation technique in the region of hypersonic flow. These data were obtained at a Mach number of 7.1, at Reynolds numbers from 0.3×10(exp 6) to 1.0×10(exp 6), and at reduced frequencies from 0.01 to 0.04. It is shown that the Embedded Newtonian theory agrees well with the experimental values including the effects of nose bluntness, angle of attack, and angle of flare on the unsteady aerodynamics of axial symmetric bodies. Also shown is that the aerodynamic damping derivative of a cone with a rotary axis Δx/l=0.292 takes the maximum value at dN/dB=0.06, when the nose bluntness is changed up to 0.3. On blunt-nose cylinder-flare bodies the effect of flare angle has been calculated by means of the approximation theory for a function of radial position in the inviscid shear flow profile.
極超音速領域における軸対称物体の動安定微係数の測定
naltr00542.pdf
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