Presents the results of sixty-six experimental flutter tests made on two uniform, cantilever wing models. Both models were fluttered over wide ranges of density. Mach number, and wave length. The data have been corrected for compressibility and wave-length effects and plotted as a function of density.NACA TN No. 1989."December 1949."Includes bibliographical references.Presents the results of sixty-six experimental flutter tests made on two uniform, cantilever wing models. Both models were fluttered over wide ranges of density. Mach number, and wave length. The data have been corrected for compressibility and wave-length effects and plotted as a function of density.Mode of access: Internet
Some of the other factors considered were found to be more or less significant however, all the fact...
Results are presented for a series of flutter studies in which a Rayleigh type analysis based on cho...
A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers betwe...
"January 1960."Cover title.Includes bibliographical references (p. 22-23).Mode of access: Internet
Flutter data in the transonic speed range for four nearly identical, thin, unswept wings have been o...
The results of the basic flutter theory originally devised in 1934 and published as NACA Technical R...
Flutter characteristics of a cantilevered high aspect ratio wing with winglet were investigated. The...
Results of flutter tests on some simple all-movable-control-type models are given. One set on models...
Low-speed flutter studies of a dynamically and elastically scaled model of a large multijet transpor...
The results of some wind-tunnel experiments to investigate the effects of aspect ratio and Mach numb...
Wind-tunnel flutter investigations at Mach numbers up to 0.30 have been conducted on a 40 degree swe...
This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that...
Subsonic and supersonic flutter calculations on swept and unswept wings to evaluate effects of varia...
Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. ...
Flutter is a catastrophic aeroelastic instability that must be prevented for all engineering structu...
Some of the other factors considered were found to be more or less significant however, all the fact...
Results are presented for a series of flutter studies in which a Rayleigh type analysis based on cho...
A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers betwe...
"January 1960."Cover title.Includes bibliographical references (p. 22-23).Mode of access: Internet
Flutter data in the transonic speed range for four nearly identical, thin, unswept wings have been o...
The results of the basic flutter theory originally devised in 1934 and published as NACA Technical R...
Flutter characteristics of a cantilevered high aspect ratio wing with winglet were investigated. The...
Results of flutter tests on some simple all-movable-control-type models are given. One set on models...
Low-speed flutter studies of a dynamically and elastically scaled model of a large multijet transpor...
The results of some wind-tunnel experiments to investigate the effects of aspect ratio and Mach numb...
Wind-tunnel flutter investigations at Mach numbers up to 0.30 have been conducted on a 40 degree swe...
This paper is concerned with a discussion of some of the problems of flutter and aeroelasticity that...
Subsonic and supersonic flutter calculations on swept and unswept wings to evaluate effects of varia...
Results of four thin, unswept, flutter airfoils attached to two freely falling bodies are reported. ...
Flutter is a catastrophic aeroelastic instability that must be prevented for all engineering structu...
Some of the other factors considered were found to be more or less significant however, all the fact...
Results are presented for a series of flutter studies in which a Rayleigh type analysis based on cho...
A flutter investigation has been made in the Langley transonic blowdown tunnel at Mach numbers betwe...