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  • 1
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    Coherent anti-Stokes Raman spectroscopy temperature measurements in a hydrogen-fueled supersonic combustor (1993)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Description: Coherent anti-Stokes Raman spectroscopy (CARS) thermometry has been used to obtain static temperature cross sections in a three-dimensional supersonic combustor flowfield. Data were obtained in three spanwise planes downstream of a single normal fuel injector which was located downstream of a rearward-facing step. The freestream flow was nominally Mach 2 and was combustion heated to a total temperature of 1440 K (yielding a static temperature of about 800 K in the freestream) to simulate the inflow to a combustor operating at a flight Mach number of about 5.4. Since a broadband probe laser was used an instantaneous temperature sample was obtained with each laser shot at a repetition rate of 10 Hz. Thus root-mean-square (rms) temperatures and temperature probability density functions (pdf's) were obtained in addition to mean temperatures.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 9; 2; p. 163-168.
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    NASA TECHNICAL REPORTS
  • 2
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    Effect of Transpiration Injection on Skin Friction in an Internal Supersonic Flow (1996)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: An experimental program was conducted at NASA Langley Research Center that included development and evaluation of an operational facility for wall drag measurement of potential scramjet fuel injection or wall cooling configurations. The facility consisted of a supersonic tunnel, with one wall composed of a series of interchangeable aluminum plates attached to an air bearing suspension system. The system was equipped with load cells that measured drag forces of 115 psia (793 kPa). This flow field contained a train of weak, unsteady, reflecting shock waves that were produced in the Mach 2 nozzle flows, the effect of reflecting shocks (which are to be expected in scramjet combustors) in internal flows has not previously been documented.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: JANNAF Combustion Subcommittee Meeting; Volume 1; 37-48; CPIA-Publ-653-Vol-1
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    NASA TECHNICAL REPORTS
  • 3
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    Effect of Cavity Injection on Wall Drag in a Supersonic Flow with Reflecting Shocks (1996)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Description: The wall drag test tunnel at NASA Langley Research Center was used to evaluate simulated scramjet fuel injection into a wall cavity. In this tunnel, one wall consists of interchangeable aluminum plates attached to an air bearing suspension system. The plates were equipped with load cells to measure drag forces and static taps to determine pressure distributions. The plates were exposed to a Mach 2 air stream at a total pressure of 115 psia (793 kPa). This flow field contained a train of weak unsteady, reflecting shock waves that were produced in the nozzle assembly located upstream of the test section.
    Keywords: Fluid Mechanics and Heat Transfer
    Type: The JANNAF Combustion Subcommittee Meeting; Volume 1; 25-36; CPIA-Publ-Vol-1
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    NASA TECHNICAL REPORTS
  • 4
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    Evaluation of parallel injector configurations for Mach 2 combustion (1992)
    In:  Other Sources
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    Publication Date: 2011-08-24
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 8; 491-499
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    NASA TECHNICAL REPORTS
  • 5
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    Lidar measurement of stratospheric dust from St. Augustine Volcano (1976)
    In:  Other Sources
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    Publication Date: 2011-08-17
    Description: The detection of a stratospheric dust layer of probable volcanic origin over Hampton, Va., on the evening of Jan. 28, 1976, with a 20-inch lidar system is reported. A digitized cathode-ray-tube trace of a return signal from altitudes of 12 to 24 km on January 28 is provided, and it is shown that 38% of the return was due to stratospheric aerosol. Noting that measurements on January 22 and February 2 showed no traces of this stratospheric dust layer, trajectories of dust-laden air parcels are followed from initiation at 0000 GMT on January 24 at the St. Augustine Volcano on Augustine Island, Alaska (59 deg N, 153 deg W). Analysis of the trajectories indicates that dust injected into the stratosphere at 59 deg N, 153 deg W could have been transported to Virginia in about 4 days. It is concluded that if the St. Augustine Volcano was the source of the dust, at least 23 deg of meridional transport from polar latitudes was observed.
    Keywords: GEOPHYSICS
    Type: American Meteorological Society; vol. 57
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  • 6
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    Dustsonde and lidar measurements of stratospheric aerosols - A comparison (1974)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Comparison of lidar and in situ measurements of stratospheric aerosol profiles obtained by backscattered ruby laser light and by direct in situ sampling over Laramie, Wyoming, on two nights in mid-September 1972. The lidar backscattering and the particle number density profiles correlated well. Based on these initial comparative experiments, the ground-based lidar coupled with temperature soundings appears to be a possible method for determining the relative aerosol profile under given stratospheric loading conditions.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Applied Optics; 13; Oct. 197
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  • 7
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    Effects of composition on acceleration induced burning-rate augmentation. (1973)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: The objective of this work was to better define the effects of propellant composition variables on the acceleration induced burning-rate augmentation of solid propellants. The rate augmentation of an aluminized propellant at a given acceleration level was found to be a nonlinear inverse function of the reference or static burning rate and not controlled by binder or catalyst type at a given reference rate. A nonaluminized and a low rate double-base propellant exhibited strong transient rate augmentation due to surface pitting resulting from the retention of hot particles on the propellant surface.
    Keywords: PROPELLANTS
    Type: AIAA Journal; 11; June 197
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  • 8
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    Effects of the acceleration vector on transient burning rate of an aluminized solid propellant. (1971)
    In:  Other Sources
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    Publication Date: 2011-08-16
    Description: Experimental results concerning the transient burning-rate augmentation of a 16% aluminum polybutadiene acrylic acid (PBAA) propellant burned in a 2-in. web motor at pressure levels from 300 to 1200 psia with centrifugal accelerations from 0 to 140 g. The orientation of the acceleration vector was varied to determine its effect on the transient burning rate. The burning-rate augmentation was strongly dependent on (1) acceleration level, (2) propellant distance burned (or burn time), and (3) orientation of the acceleration vector with respect to the burning surface. This transient rate augmentation resulted from the retention of molten metallic residue on the burning surface by the normal acceleration loading. The presence of the residue altered the combustion zone heat transfer and caused increased localized burning rates, as evidenced by the pitted propellant surfaces that were observed from extinction tests conducted at various acceleration levels.
    Keywords: PROPELLANTS
    Type: Journal of Spacecraft and Rockets; 8; Nov. 197
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  • 9
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    Numerical predictions of a rearward-facing-step flow in a supersonic combustor (1989)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Propulsion and Power (ISSN 0748-4658); 5; 158-164
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  • 10
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    Supersonic combustion of a silane/methane mixture (1985)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A test program was conducted to evaluate the ignition and combustion characteristics of a 20 volume percent silane/methane mixture using a model scramjet combustor with Mach 2 combustor entrance conditions. The test gas total temperature was varied from 1200 to 3900 R. The mixture autoignited at a total temperature of 1650 R. This autoignition temperature can be contrasted with 2330 R for hydrogen and 1350 R for a 20 percent silane/hydrogen mixture in similar hardware. Methane without the silane additive did not autoignite in this configuration at temperatures as high as 3900 R.
    Keywords: INORGANIC AND PHYSICAL CHEMISTRY
    Type: JHU, The 22nd JANNAF Combustion Meeting, Vol. 1; p 411-416
    Format: text
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