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At least 1,315 records · Page 73

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NASA NTRS1992

Improved Depiction Of Computed Unsteady Flows

PLOT4D and STREAKER programs increase ease of production and utility of animated depictions of unsteady flows simulated numerically by advanced computational fluid dynamics. Programs developed to maximize information displayed while minimizing amount stored. PLOT4D, an extended version of PLOT3D, used to depict steady three-dimensional flows, incorporates features making it more computationally efficient than to visualize unsteady flow as succession of steady flows, animating frame by frame. PLOT4D postprocesses numerical output of fluid-dynamical computation into maps of flow quantities on two-coordinate surfaces depicting cut through flow field or conform to body surface. STREAKER generates streaklines, close approximations of patterns traced by streams of dye or smoke released into simulated flows. Streaklines defined via spatial succession of endpoints of pathlines of massless particles released into flow. STREAKER computes endpoints by fourth-order Runge-Kutta integration of velocity vectors.

Smith, Merritt H.↗

NASA NTRS1990

In-flight flow visualization and pressure measurements at low speeds on the NASA F-18 high alpha research vehicle

Inflight results from surface and off surface flow visualizations and from extensive pressure distributions document the vortical flow on the leading edge extensions (LEXs) and forebody of the NASA F-18 high alpha research vehicle (HARV) for low speeds and angles of attack up to 50 deg. Surface flow visualization data, obtained using the emitted fluid technique, were used to define separation lines and laminar separation bubbles (LSB). Off surface flow visualization data, obtained by smoke injection, were used to document both the path of the vortex cores and the location of vortex core breakdown. The location of vortex core breakdown correlated well with the loss of suction pressure on the LEX and with the flow visualization results from ground facilities. Surface flow separation lines on the LEX and forebody corresponded well with the end of pressure recovery under the vortical flows. Correlation of the pressures with wind tunnel results show fair to good correlation.

John H Del Frate↗

NASA NTRS1991

Risks, designs, and research for fire safety in spacecraft

Current fire protection for spacecraft relies mainly on fire prevention through the use of nonflammable materials and strict storage controls of other materials. The Shuttle also has smoke detectors and fire extinguishers, using technology similar to aircraft practices. While experience has shown that the current fire protection is adequate, future improvements in fire safety technology to meet the challenges of long duration space missions, such as the Space Station Freedom, are essential. All spacecraft fire protection systems, however, must deal with the unusual combustion characteristics and operational problems in the low gravity environment. The features of low gravity combustion that affect spacecraft fire safety, and the issues in fire protection for Freedom that must be addressed eventually to provide effective and conservative fire protection systems are discussed.

Friedman, Robert↗

NASA NTRS1992

The flip-flop nozzle extended to supersonic flows

An experiment studying a fluidically oscillated rectangular jet flow was conducted. The Mach number was varied over a range from low subsonic to supersonic. Unsteady velocity and pressure measurements were made using hot wires and piezoresistive pressure transducers. In addition smoke flow visualization using high speed photography was used to document the oscillation of the jet. For the subsonic flip-flop jet it was found that the apparent time-mean widening of the jet was not accompanied by an increase in mass flux. It was found that it is possible to extend the operation of these devices to supersonic flows. Most of the measurements were made for a fixed nozzle geometry for which the oscillations ceased at a fully expanded Mach number of 1.58. By varying the nozzle geometry this limitation was overcome and operation was extended to Mach 1.8. The streamwise velocity perturbation levels produced by this device were much higher than the perturbation levels that could be produced using conventional excitation sources such as acoustic drivers. In view of this ability to produce high amplitudes, the potential for using small scale fluidically oscillated jet as an unsteady excitation source for the control of shear flows in full scale practical applications seems promising.

Raman, Ganesh↗

NASA NTRS1992

Wind-tunnel static and free-flight investigation of high-angle-of-attack stability and control characteristics of a model of the EA-6B airplane

An investigation was conducted in the Langley 30- by 60-Foot Tunnel and the Langley 12-Foot Low-Speed Tunnel to identify factors contributing to a directional divergence at high angles of attack for the EA-6B airplane. The study consisted of static wind-tunnel tests, smoke and tuft flow-visualization tests, and free-flight tests of a 1/8.5-scale model of the airplane. The results of the investigation indicate that the directional divergence of the airplane is brought about by a loss of directional stability and effective dihedral at high angles of attack. Several modifications were tested that significantly alleviate the stability problem. The results of the free-flight study show that the modified configuration exhibits good dynamic stability characteristics and could be flown at angles of attack significantly higher than those of the unmodified configuration.

Jordan, Frank L., Jr.↗

NASA NTRS1992

An Extention of the Raman-lidar Technique to Measure the Velocity and Temperature of the Atmospheric Emission Jets from Stacks

If a Raman lidar possesses a proper spatial resolution sufficient for acquiring profiles of return signals across an emission jet, then the difference in number densities of nitrogen molecules within the jet and outside it will cause a dip in the lidar return signal from nitrogen. Experimentation showed that the Raman lidar technique can accurately measure the velocity and temperature of atmospheric emission from smoke stacks.

Arshinov, Yu. F.↗

NASA NTRS1991

Nuclear winter - Physics and physical mechanisms

The basic physics of the environmental perturbations caused by multiple nuclear detonations is explored, summarizing current knowledge of the possible physical, chemical, and biological impacts of nuclear war. Emphasis is given to the impact of the bomb-generated smoke (soot) particles. General classes of models that have been used to simulate nuclear winter are examined, using specific models as examples.

Turco, R. P.↗

NASA NTRS1992

Aircraft control at high-alpha by tangential blowing

An experimental study has been undertaken to investigate the possibility of using tangential blowing to provide control forces and moments on a delta wing-forebody combination at high angles of attack. The present model can utilize the blowing separately on the wing and forebody. This research emphasizes the effect of blowing on the aerodynamics of the state of the art model by using: (1) flow visualization (smoke-flow visualization using a laser sheet), and (2) force and moment measurements. Experiments revealed that the effect of the blowing on a body-wing combination differs in several respects compared to that of wing alone or body alone. Force and moment measurements on the present model showed that the asymmetric blowing from the fuselage creates larger side force, rolling and yawing moments compared to blowing from the wing. In the presence of the forebody, the effectiveness of the rolling moment generated by blowing from the wing is reduced.

Celik, Zeki Z.↗

NASA NTRS1992

Natural convection in binary gases driven by combined horizontal thermal and vertical solutal gradients

An investigation of natural convection is presented to examine the influence of a horizontal temperature gradient and a concentration gradient occurring from the bottom to the cold wall in a cavity. As the solutal buoyancy force changes from augmenting to opposing the thermal buoyancy force, the fluid motion switches from unicellular to multicellular flow (fluid motion is up the cold wall and down the hot wall for the bottom counterrotating flow cell). Qualitatively, the agreement between predicted streamlines and smoke flow patterns is generally good. In contrast, agreement between measured and predicted temperature and concentration distributions ranges from fair to poor. Part of the discrepancy can be attributed to experimental error. However, there remains considerable discrepancy between data and predictions due to the idealizations of the mathematical model, which examines only first-order physical effects. An unsteady flow, variable thermophysical properties, conjugate effects, species interdiffusion, and radiation were not accounted for in the model.

Weaver, J. A.↗

NASA NTRS1992

Unsteady wing surface pressures in the wake of a propeller

The unsteady nature of the propeller slipstream interacting with a wing has been studied by flow visualization and unsteady wing surface pressure measurements. Flow visualization was performed by marking the propeller tip vortex with smoke. Unsteady wing surface pressures were measured by traversing a wing instrumented with a chordwise array of 16 microphones in a spanwise direction through the propeller wake. This work yielded information on the motion of the propeller wake as it passes over the wing. As the propeller wake passed over the wing: the propeller tip vortex experienced an inviscid interaction at the leading edge; viscous action at the leading edge severed the propeller tip vortex; the propeller tip vortex experienced significant spanwise and chordwise displacements and then deformed in order to reconnect at the trailing edge; axial velocity in the vortex core caused the helical vortex to thicken or stretch near the wing surface; and, the magnitude of the pressure fluctuations decreased in magnitude with distance traveled along the chord.

Johnston, R. T.↗

NASA NTRS1992

Evaluation of a technique for satellite-derived area estimation of forest fires

The advanced very high resolution radiometer (AVHRR), has been found useful for the location and monitoring of both smoke and fires because of the daily observations, the large geographical coverage of the imagery, the spectral characteristics of the instrument, and the spatial resolution of the instrument. This paper will discuss the application of AVHRR data to assess the geographical extent of burning. Methods have been developed to estimate the surface area of burning by analyzing the surface area effected by fire with AVHRR imagery. Characteristics of the AVHRR instrument, its orbit, field of view, and archived data sets are discussed relative to the unique surface area of each pixel. The errors associated with this surface area estimation technique are determined using AVHRR-derived area estimates of target regions with known sizes. This technique is used to evaluate the area burned during the Yellowstone fires of 1988.

Cahoon, Donald R., Jr.↗

NASA NTRS1991

Emissions of nitrous oxide from biomass burning

A study has been conducted which compared N2O results obtained over large prescribed fires or wildfires, in which 'grab-sampling' with storage had been used with N2O measurements made in near-real time. CO2-normalized emission ratios obtained initially from the laboratory fires are substantially lower than those obtained over large-scale biomass fires. Combustion may not be the only source of N2O in large fire smoke plumes; physical, chemical, and biochemical processes in the soil may be altered by large biomass fires, leading to large N2O releases.

Winstead, Edward L.↗

NASA NTRS1992

The flip flop nozzle extended to supersonic flows

Raman, Ganesh↗

NASA NTRS1992

Earth observations on Space Shuttle Flight 43 - It was a dirty world

Attention is given to earth observations made by the crew of Space Shuttle Flight 43, during which atmospheric haze and its various aerosols were investigated. The length-of-record time series from the Space Shuttle Earth Observation Program was used to photograph some of the sites under active investigation. It was found that Lake Chad's northern basin remained dry, and the southern basin showed no appreciable changes in water level. The Okavango Swamp areas in Botswana showed agricultural burning at several sites, and increasing evidence of land use activity in the areas of the swamp that previously had been under natural cover. Consideration is also given to Hurricane Fefa and Tropical Storm Guillermo, the smoke from the Kuwaiti oil fires, Mount Pinatubo, dust storms in the Sahara, biomass burning, South Asian monsoon runoff, land use patterns, landforms and geology, and oceans and coastal features.

Amsbury, David L.↗

NASA NTRS1992

Cosmic dust analogue material condensation in microgravity: The Stardust programme - First results and future activities

Initial results are presented from airborne experiments investigating the vapor phase condensation in microgravity, carried out in the framework of the Stardust international program. Special attention is given to the design and operation of the experimental equipment, which includes the furnace for producing vapors from different materials and the cloud chamber in which the vapor nucleation occurs. A two-part mathematical model was developed to describe the transport processes in the nucleation chamber. Results obtained from three experimental series were conducted with Mg and Zn aboard NASA's KC-135 reduced-gravity research aircraft showed that nucleation front (smoke cloud) was quite different in appearance in microgravity from that typically observed at 1-g condition. The Mg and Zn particles exhibited significant differences in shape; there was some evidence of coagulation.

Ferguson, F.↗

NASA NTRS1993

Vapor-Generator Wand Helps To Reveal Airflow Patterns

In vapor-generator wand, liquid propylene glycol flows into electrically heated stainless-steel tube. Liquid boils in heated tube, and emerging vapor forms dense, smoke-like fog used to make airflow patterns visible. Built in variety of sizes, suitable for uses ranging from tabletop demonstrations to research in wind tunnels. For best viewing, plume illuminated by bright, focused incandescent spotlight at right angle to viewing direction. Viewing further enhanced by coating walls of test chamber with flat, dark color to minimize reflections and increase contrast.

Robelen, David B.↗

NASA NTRS1992

In-flight flow visualization results from the X-29A aircraft at high angles of attack

Flow visualization techniques were used on the X-29A aircraft at high angles of attack to study the vortical flow off the forebody and the surface flow on the wing and tail. The forebody vortex system was studied because asymmetries in the vortex system were suspected of inducing uncommanded yawing moments at zero sideslip. Smoke enabled visualization of the vortex system and correlation of its orientation with flight yawing moment data. Good agreement was found between vortex system asymmetries and the occurrence of yawing moments. Surface flow on the forward-swept wing of the X-29A was studied using tufts and flow cones. As angle of attack increased, separated flow initiated at the root and spread outboard encompassing the full wing by 30 deg angle of attack. In general, the progression of the separated flow correlated well with subscale model lift data. Surface flow on the vertical tail was also studied using tufts and flow cones. As angle of attack increased, separated flow initiated at the root and spread upward. The area of separated flow on the vertical tail at angles of attack greater than 20 deg correlated well with the marked decrease in aircraft directional stability.

Delfrate, John H.↗

NASA NTRS1992

Findings of a review of spacecraft fire safety needs

Discussions from a workshop to guide UCLA and NASA investigators on the state of knowledge and perceived needs in spacecraft fire safety and its risk management are reviewed, for an introduction to an analytical and experimental project in this field. The report summarizes the workshop discussions and includes the visual aids used in the presentations. Probabilistic Safety Assessment (PSA) methods, which are currently not used, would be of great value to the designs and operation of future human-crew spacecraft. Key points in the discussions were the importance of understanding and testing smoldering as a likely fire scenario in space and the need for smoke damage modeling, since many fire-risk models ignore this mechanism and consider only heat damage.

Apostolakis, G. E.↗