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Harry's War
Harry's War: A World War II Memoir, the story of the USAAF's 30th Photo Reconnaissance Squadron, comes to life with 150 photographs. Harry's War is an engaging personal story about World War II aviation. Captain Harry Runyan served with the 30th Photo Reconnaissance Squadron, US Army Air Forces, in the European theater, collecting hundreds upon hundreds of photographs during his duty overseas. These stunning, thought-provoking images of planes, places, men, and battlefields come together to tell the tale of an oft-overlooked, yet extremely vital fact of how the Allies achieved victory in Europe. Harry's War shares stories about logistics, aerial reconnaissance, aircraft, jets, and rockets, a...
Single-degree-of-freedom-flutter Calculations for a Wing in Subsonic Potential Flow and Comparison with an Experiment
The effect of Mach number and structural damping on single-degree-of-freedom pitching of a wing is presented in this report. Some experimental results are compared with theory and good agreement is found for certain ranges of an inertia parameter.
Considerations on the Effect of Wind-tunnel Walls on Oscillating Air Forces for Two-dimensional Subsonic Compressible Flow
This paper treats the effect of wind-tunnel walls on the oscillating two-dimensional air forces in a compressible medium. The walls are simulated by the usual method of placing impages at appropriate distances above and below the wing. An important result shown is that, for certain conditions of wing frequency, tunnel height, and Mach number, the tunnel and wing may form a resonant system so that the forces on the wing are greatly changed from the condition of no tunnel walls.
NASA Technical Note
None
Theoretical and Experimental Investigation of the Effect of Tunnel Walls on the Forces on an Oscillating Airfoil in Two-dimensional Subsonic Compressible Flow
This paper presents a theoretical and experimental investigation of the effect of wind-tunnel walls on the air forces on an oscillating wing in two-dimensional subsonic compressible flow. A method of solving an integral equation which relates the downwash on a wing to the unknown loading is given, and some comparisons are made between the theoretical results and the experimental results. A resonance condition, which was predicted by theory in a previous report (NACA Rep. 1150), is shown experimentally to exist. In addition, application of the analysis is made to a number of examples in order to illustrate the influence of walls due to variations in frequency of oscillation, Mach number, and ratio of tunnel height to wing semichord.
On the Kernel Function of the Integral Equation Relating the Lift and Downwash Distributions of Oscillating Finite Wings in Subsonic Flow
The derivation of the integral equation which involves this kernel function, originally performed elsewhere (see, for example, NACA Technical Memorandum 979) is reproduced as an appendix. A second appendix gives the reduction of the form of the kernel function obtained herein for the three-dimensional case to a known result of Possio for two-dimensional flow.
Report
None
Effect of High-velocity Fluid Flow on the Bending Vibrations and Static Divergence of a Simply Supported Pipe
The present experimental study is concerned with the effect of high velocity fluid flow on the static and dynamic characteristics of a simply supported pipe.
