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Volume 24, Issue 266
Displaying 1-6 of 6 articles from this issue
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Ryojiro AKIBA, Hiroki MATHUO1976 Volume 24 Issue 266 Pages 103-113
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
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Chikara MURAKAMI1976 Volume 24 Issue 266 Pages 114-120
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
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Kimio KANAI1976 Volume 24 Issue 266 Pages 121
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
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Shingo NAKAMURA, Makoto KOBAYAKAWA1976 Volume 24 Issue 266 Pages 122-132
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
JOURNAL FREE ACCESSThe sinusoidal gust response of a wing which is flying in the vicinity of the ground was investigated theoretically and experimentally. Theoretically, the gust response functions of a lowaspect ratio wing were calculated applying LAWRENCE'S method of an oscillating wing. In this case, the lift force augmentation by the ground effect was obtained by the image wing technique.
The experiments were performed by wind tunnel tests. That is to say, the sinusoidal gust was generated in the wind tunnel, and this gusty flow stroke the wing model. Then, the gust velocity and lift force fluctuation were mesured simultaneously.
The lift force augmentation which was expressed by the ratio of response function with ground to that without ground was compared with that of the theoretical value.
It is found that both of them agree well with each other for several case. Consequently, it may be said that the theoretical values in this paper can estimate the ground effect on the gust response of a wing pretty well. However, it would be difficult to investigate this problem more precisely by perturbation theory, since the gust velocity distribution becomes shear flow and linearity assumption would not hold in the vicinity of the ground.View full abstractDownload PDF (521K) -
Taketoshi HANAWA, Yoichi HAYASHI, Yasuo TADA, Susumu TODA, Kazuo KUSAK ...1976 Volume 24 Issue 266 Pages 132-144
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
JOURNAL FREE ACCESSIn this paper the authors applied the wellknown RAYLEIGH-RITZ'S procedure to the analysis of natural vibration characteristics of plate beam combination structures.
General analytical equations were formulated for the structures which consisted of built-up wings and a fuselage. The vibration tests were done on the cantilevered wing, freely suspended built-up delta wing and the built-up delta wings with the fuselage which structurally simulated free-flight model FFM-102) designed to investigate the dynamic characteristics in supersonic flight. The results of the tests were compared with the results obtained from analysis formulated.
It was found that both results were in good agreements. It may be concluded that this analytical method is one of the usefull methods for predicting the natural vibration caracteristics of such structures.View full abstractDownload PDF (1739K) -
Tomoari NAGASHIMA, Ken'ichi NISHIJIMA1976 Volume 24 Issue 266 Pages 145-152
Published: March 05, 1976
Released on J-STAGE: May 25, 2009
JOURNAL FREE ACCESSThe dynamical similarity rules for rigid and articulated rotor blades with a pitch angle are derived.
The blade dynamics is described as a linear and elastically coupled vibration system which contains three typical similarity parameters, whose eigen values and eigen functions are numerically determined by the power method.
It is found that the effects of the similarity parameters on the vibration characteristics are more dominant for a rigid blade than for an articulated one.
It is also shown that dynamical simulation techniques for a rotor blade become easier if composite materials which have high modulus to density ratio, E/ρ, could be utilised.View full abstractDownload PDF (439K)
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