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This report deals with a description and report of tests carried out at the Washington Navy Yard on models of the RAF-6, albatross and Slone airfoils to determine the effectiveness of the conventional wing-trailing edge being always longer than the leading edge. The results are compared with the values computed by standard formulae in use at the time the tests were conducted.
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In one scenario of a crack in an airplane fuselage, the crack is subjected to cyclic tensile and out of plane shearing loads. To predict the fatigue crack growth in such a situation, experiments are being performed to measure the crack growth rate in laboratory specimens subjected to similar loadings. The mechanics of this problem are reviewed, the energy release rate is calculated and designs for an experiment are discussed along with some preliminary experimental observations.
We employ the opposed flow flame-spread configuration in order to examine flame-front instability of diffusion flames near cold, solid boundaries. The thermo-diffusive and hydrodynamic instabilities can transform an initially planar flame front into an irregularly curved, corrugated, possibly fragmented front. Under ordinary 1-g conditions, the buoyancy-induced flow masks the thermo-diffusive and hydrodynamic instabilities and produces planar flames. Such stable spreading flames have been observed for decades in laboratory experiments. Experiments in zero gravity are necessary to produce unstable flame fronts. The thermo-diffusive/hydrodynamic microgravity instability appears in diffusion flames such as, for example: the candle flame oscillations observed by Dietrich et al.; smolder instabilities on a recent Space Shuttle flight. Drs. T. Kashiwagi and S. Olson have attributed the latter to a lowered oxygen transport rate to the hot, reactive surface. Consider a burning surface near the flame extinction limit. The flow, or stretch, induced by the diffusion flame is weak, hence buoyancy plays a small role, thereby enabling previously secondary mechanisms, such as differential thermo-diffusion, to become the most important mechanisms. The flame leading edge becomes unstable; and diffusion flame breakup, oscillation, and rejoining all occur at a measurable frequency of approximately O(1 Hz). This project has only begun in January of this year, 1999. To date, there have been no flight experiments on flame spread instabilities. However, we have made numerous experiments in the NASA 2.2 and 5 second drop towers on flame spread over very thin cellulosic fuels. We have been very fortunate through a combination of factors, to be explained, to obtain some interesting, perhaps even compelling, results on diffusion flame instability in the presence of heat losses to cold surfaces.
Power, wing angle of attack, and the angle of the duct relative to the wing were varied to achieve a specified lift and thrust for a forward velocity range from 0 to 140 knots. In this manner a so-called transition program of steady-state conditions was defined over the velocity range. It was found-that large pitch-up moments resulted when the ducted fan was operated at an angle of attack to the air stream. A deflected vane installed in the high-energy air at the duct exit was helpful in reducing these pitch-up moments. Large downwash angles were induced by the ducted fan at a selected horizontal-tail location. The possibility of using guide vanes in the duct inlet to vary thrust for the purpose of roll control at low forward speeds was examined.The maximum incremental thrust available at zero forward velocity was found to be 11% of the total thrust required at that speed.
For over thirty years now, the H-46 Sea Knight tandem rotor helicopter has operated successfully from the decks of various U.S. Navy ships. There have been approximately 210 thousand landings and takeoffs at sea and the vast majority have occurred without incident. Only a small percent of the total H-46 landings and takeoffs have been less than fully satisfactory. On certain ships, (e.g. the LHA amphibious assault ship) the combination of winds at 15 deg. or so off of the bow and low rotor r.p.m. are conditions under which, on occasion, the rear rotor blades have been observed to flap uncontrollably. Cases have been reported where the rotor blades have struck the H-46 sync-shaft cover during startup and shutdown while the H-46 is sitting on the deck. One life has been lost, several people injured and the repair costs total of the 110+ incidents has been estimated to exceed $20 million. To date, the root cause of this problem has not been identified.
As an activist for the project community at NASA's Ames Research Center, I see my role as finding out what resource project managers need to help them run successful projects. I need to go out and advocate for those resources, if necessary, and I need to be supportive, not just for the projects, but also for the project managers and their teams. It's not something I can do sitting at my desk waiting for the phone to ring. To me, that's what an activist does. It's public service. In this case my public is the project-practitioner community.
Gravity sensing in plants and algae is hypothesized to rely upon either the mass of the entire cell or that of sedimenting organelles (statoliths). Protonemata of the moss Ceratodon purpureus show upward gravitropism and contain amyloplasts that sediment. If moss sensing were whole-cell based, then media denser than the cell should prevent gravitropism or reverse its direction. Cells that were inverted or reoriented to the horizontal displayed distinct negative gravitropism in solutions of iodixanol with densities of 1.052 to 1.320 as well as in bovine serum albumin solutions with densities of 1.037 to 1.184 g cm(-3). Studies using tagged molecules of different sizes and calculations of diffusion times suggest that both types of media penetrate through the apical cell wall. Estimates of the density of the apical cell range from 1.004 to 1.085. Because protonemata grow upward when the cells have a density that is lower than the surrounding medium, gravitropic sensing probably utilizes an intracellular mass in moss protonemata. These data provide additional support for the idea that sedimenting amyloplasts function as statoliths in gravitropism.
RNA-binding proteins, which are involved in the synthesis, processing, transport, translation, and degradation of RNA, are emerging as important, often multifunctional, cellular regulatory proteins. Although relatively few RNA-binding proteins have been studied in plants, they are being identified with increasing frequency, both genetically and biochemically. RNA-binding proteins that regulate chloroplast mRNA stability and translation in response to light and that have been elegantly analyzed in Clamydomonas reinhardtii have counterparts with similar functions in higher plants. Several recent reports describe mutations in genes encoding RNA-binding proteins that affect plant development and hormone signaling.
A new formulation of helicopter rotor thickness, noise for hover and forward flight, is discussed. The parameters required for this formulation are rotor motion, planform and airfoil thickness distribution. A computer program has been developed to calculate the pressure signature due to blade thickness for a helicopter in arbitrary motion. Comparison with high-speed helicopter tests shows good agreement with calculations when the observer is in or near the horizontal plane in which the rotor disc lies. Characteristics of thickness noise are illustrated by numerical examples indicating strongly that the high-speed blade slap may be due primarily to the thickness effect. The methods of Deming and Arnoldi are discussed as the special cases of this technique.
The contents of this CD-ROM include: 1) Aero Data; 2) Data Documents (Daily Acoustic Data Logs, Test Documentation, Test Photos); 3) EPNL Data (All Core Tones Removed, All Core Tones Removed and Various Bypass Tones, Core BPF Tone Removed, Core Tones Present); 4) Far-Field Acoustic Data, 5) High Speed Fan Reports; 6) Sound Power Levels (As-Measured PWL, Lossless PWL).
The Multi-angle Imaging Spectro-Radiometer aboard Terra calibration and validation team at JPL employs a suite of ground based radiance measurements to derive multi-angle TOA radiance predictions.
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