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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.

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At least 163 records · Page 9

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NASA NTRS1974

The effect of engine component noise on V/STOL aircraft noise contours

An analytical study of fly-over noise using noise contours to show the effects of varying airplane and path parameters. The method of approach was to synthesize engine component noise spectra and exercise these components along given flight paths to measure the individual and total fly-over effect as a function of noise footprint area. The study was carried out in two phases. Phase 1 utilized a research type aircraft and Phase 2 used an advanced VTOL aircraft. The effect of cross flow was considered for both inlet and exhaust sections of the engine.

Fogg, R. G.↗

NASA NTRS1974

Flight Reynolds number effects on a contoured boattail nozzle at subsonic speeds

A contoured boattail nozzle typical of those used on a twin-engine fighter was tested on an underwing nacelle mounted on an F-106B aircraft. The gas generator was a J85-GE-13 turbojet engine. The effects of Reynolds number, Mach number, and angle of attack on boattail drag and boattail pressure profiles were investigated. Increasing Reynolds number caused a slight reduction in boattail drag at both Mach 0.7 and 0.9. The nozzle had relatively low boattail drag even though the flow was separated over a large portion of the boattail.

Chamberlin, R.↗

NASA NTRS1975

Simple computer method provides contours for radiological images

Computer is provided with information concerning boundaries in total image. Gradient of each point in digitized image is calculated with aid of threshold technique; then there is invoked set of algorithms designed to reduce number of gradient elements and to retain only major ones for definition of contour.

Newell, J. D.↗

NASA NTRS1974

A simple method for the generation of organ and vessel contours from roentgenographic or fluoroscopic images

A simple method for outlining or contouring any area defined by a change in film density or fluoroscopic screen intensity is described. The entire process, except for the positioning of an electronic window, is accomplished using a small computer having appropriate softwave. The electronic window is operator positioned over the area to be processed. The only requirement is that the window be large enough to encompass the total area to be considered.

Newell, J. D.↗

NASA NTRS1975

Digital computer programs for generating oblique orthographic projections and contour plots

User and programer documentation is presented for two programs for automatic plotting of digital data. One of the programs generates oblique orthographic projections of three-dimensional numerical models and the other program generates contour plots of data distributed in an arbitrary planar region. A general description of the computational algorithms, user instructions, and complete listings of the programs is given. Several plots are included to illustrate various program options, and a single example is described to facilitate learning the use of the programs.

Giles, G. L.↗

NASA NTRS1975

Effects of forward contour modification on the aerodynamic characteristics of the NACA 641-212 airfoil section

Two different forward contour modifications designed to increase the maximum lift coefficient of the NACA 64 sub 1-212 airfoil section were evaluated experimentally at low speeds. One modification consisted of a slight droop of the leading edge with an increased leading-edge radius; the other modification incorporated increased thickness over the forward 35 percent of the upper surface of the profile. Both modified airfoil sections were found to provide substantially higher maximum lift coefficients than the 64 sub 1-212 section. The drooped leading-edge modification incurred a drag penalty of approximately 10 percent at low and moderate lift coefficients and exhibited a greater nosedown pitching moment than the 64 sub 1-212 profile. The upper surface modification produced about the same drag level as the 64 sub 1-212 section at low and moderate lift coefficients and less nosedown pitching moment than the 64 sub 1-212 profile. Both modified airfoil sections had lower drag coefficients than the 64 sub 1-212 section at high lift coefficients.

Hicks, R. M.↗

NASA NTRS1977

A FORTRAN program for the determination of nozzle contours for rotational, non-homentropic gas mixtures

A program was written which generates a nozzle contour and the complete flow field for two dimensional or axisymetric flows designed to exit parallel to the axis at uniform pressure. The flow is that of a rotational, non-homentropic gas mixture where viscous effects were neglected and the chemistry is assumed frozen. A description of the numerical program developed, is also described.

Kalben, P.↗

NASA NTRS1977

Comparison of jet Mach number decay data with a correlation and jet spreading contours for a large variety of nozzles

Small-scale circular, noncircular, single- and multi-element nozzles with flow areas as large as 122 sq cm were tested with cold airflow at exit Mach numbers from 0.28 to 1.15. The effects of multi-element nozzle shape and element spacing on jet Mach number decay were studied in an effort to reduce the noise caused by jet impingement on externally blown flap (EBF) STOL aircraft. The jet Mach number decay data are well represented by empirical relations. Jet spreading and Mach number decay contours are presented for all configurations tested.

Groesbeck, D. E.↗

NASA NTRS1977

The influence of the inlet duct contour on forward radiated fan noise

Measurements have been obtained to determine the extent to which the shape of the inlet duct affects the directivity pattern of forward radiated noise from aircraft gas turbine engines. The test program was conducted using a model fan to which were attached any of three inlet ducts with each designed to cause a particular noise directivity pattern. Existing information on the effects of wave refraction in inlet-type flow fields was used to design the duct contours. Results indicated that the shape of the inlet duct strongly influenced the radiated noise field but that wave refraction was not the dominant factor in controlling the noise directivity pattern.

Sloan, D.↗

NASA NTRS1979

Holding fixture for variable-contour parts

Array of vacuum cups on spindles holds parts for safe machining and other processings. Variable-contour part resting on fixture is held firmly enough for machining, coating, or other mechanical treatment.

Haynie, C. C.↗

NASA NTRS1978

Effect of leading-edge contour and vertical-tail configuration on the low-speed stability characteristics of a supersonic transport model having a highly-swept arrow wing

A low-speed investigation was made on a highly-swept arrow-wing model to determine the effect of wing leading-edge contour and vertical-tail configuration on the aerodynamic characteristics in pitch and sideslip. The investigation was made with the trailing-edge flaps deflected over a range of angles of attack from 8 deg to 32 deg. The tests were made at a Mach number of 0.13, which corresponds to a Reynolds number of about 3,000,000 based on the wing reference chord.

Lockwood, V. E.↗

NASA NTRS1978

Device for measuring the contour of a surface

Light from a source is imaged by a lens onto a surface so that the energy from the source is concentrated into a spot. As the spot across the surface is scanned, the surface moves relative to the point of perfect focus. When the surface moves away from perfect focus the spot increases in size, while the total energy in the spot remains virtually constant. The lens then reimages the light reflected by the surface onto two detectors through two different sized apertures. The light energy going to the two detectors is separated by a beam splitter. This second path of the light energy through the lens further defocuses the spot, but as a result of the different sizes of the apertures in each light detector path, the amount of defocus for each is different. The ratio of the outputs of the two detectors which are indicative of the contour of the surface is obtained by a divider.

Burcher, E. E.↗

NASA NTRS1978

Synthesis of a laterally displaced cluster feed for a reflector antenna with application to multiple beams and contoured patterns

Two methods are described for efficiently synthesizing the excitation coefficients of a laterally displaced cluster feed in a reflector antenna subject to beam distortion. Applications are presented for rotationally symmetric paraboloids excited by an equilateral triangular array of feed elements. The basic cluster is a central element surrounded by a hexagonal ring. The first method - termed the sequential current method - determines a set of excitation coefficients which minimizes the phase distortion in the 'effective' aperture distribution of the reflector. The second method - termed the gradient optimization method - is such that the distortion in the secondary power pattern is directly minimized in a min-L2 form by a gradient optimization algorithm regarded as a systematic computer iteration procedure. Application to the synthesis of contour patterns is included.

Galindo-Israel, V.↗

NASA NTRS1980

Gage for 3-d contours

Simple gage, used with template, can help inspectors determine whether three-dimensional curved surface has correct contour. Gage was developed as aid in explosive forming of Space Shuttle emergency-escape hatch. For even greater accuracy, wedge can be made of metal and calibrated by indexing machine.

Haynie, C. C.↗

NASA NTRS1980

Generalized plotting and contouring package

PLOTPAK is complete general purpose plotting and contouring package. Flexible and easy-to-use system, it produces line-printer, television-screen, and DICOMED plots. Plots, from quick and simple to complex and sophisticated, can be generated with only basic knowledge of FORTRAN and PLOTPAK commands.

Rubin, D.↗

NASA NTRS1978

Analytical design of a contoured wind-tunnel liner for supercritical testing

The present analytical design procedure is being developed in order to determine the shape of a contoured nonporous wind tunnel liner for use in the Ames 12-foot pressure wind tunnel test of a large chord, laminar flow control, swept wing panel which has a supercritical airfoil section. This procedure is applicable to the two-dimensional streamlined tunnel problem wall shape with that found experimentally.

Newman, P. A.↗

NASA NTRS1979

User guide for STRMLN: A boundary-layer program for contoured wind-tunnel liner design

A 2-D boundary layer computer code developed to process data for an arbitrary number of streamlines is presented. Provisions are included for the computer code to determine either mass transfer rates necessary for an effective boundary layer displacement of zero thickness or the effective displacement thickness for a specified mass transfer-rate distribution. The computer code was developed to be compatible with other computer codes which are being modified and/or developed at the NASA-Langley Research Center in order to design the three dimensional, contoured, wind tunnel liner used in transonic testing of a laminar flow control system installed on a supercritical airfoil section. A brief discription of the liner design procedure, representative liner calculations, adaptive-wall design for a two dimensional wind tunnel test, and other applications are reported.

Anderson, E. C.↗

NASA NTRS1978

A comparison of contour maps derived from independent methods of measuring lunar magnetic fields

Computer-generated contour maps of strong lunar remanent magnetic fields are presented and discussed. The maps, obtained by previously described (Eliason and Soderblom, 1977) techniques, are derived from a variety of direct and indirect measurements from Apollo 15 and 16 and Explorer 35 magnetometer and electron reflection data. A common display format is used to facilitate comparison of the maps over regions of overlapping coverage. Most large scale features of either weak or strong magnetic field regions are found to correlate fairly well on all the maps considered.

Lichtenstein, B. R.↗