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Operating Characteristics of the Lauterbach and Dautrebande Aerosol Generators

Description: From Abstract: "The air flow through the jet, the effect of a pre-humidifier on the water vapor content of the jet air, the cooling effect of the jet air on the generator solution, and the amount of water vapor carried away by the jet air were also determined and the results are discussed."
Date: February 1963
Creator: Mercer, T. T.; Tillery, M. I. & Flores, M. A.
Partner: UNT Libraries Government Documents Department

Modified Fragmentation Function from Quark Recombination

Description: Within the framework of the constituent quark model, it isshown that the single hadron fragmentation function of a parton can beexpressed as a convolution of shower diquark or triquark distributionfunction and quark recombination probability, if the interference betweenamplitudes of quark recombination with different momenta is neglected.Therecombination probability is determined by the hadron's wavefunction inthe constituent quark model. The shower diquark or triquark distributionfunctions of a fragmenting jet are defined in terms of overlappingmatrices of constituent quarks and parton field operators. They aresimilar in form to dihadron or trihadron fragmentation functions in termsof parton operator and hadron states. Extending the formalism to thefield theory at finite temperature, we automatically derive contributionsto the effective single hadron fragmentation function from therecombination of shower and thermal constituent quarks. Suchcontributions involve single or diquark distribution functions which inturn can be related to diquark or triquark distribution functions via sumrules. We also derive QCD evolution equations for quark distributionfunctions that in turn determine the evolution of the effective jetfragmentation functions in a thermal medium.
Date: July 26, 2005
Creator: Majumder, A.; Wang, Enke & Wang, Xin-Nian
Partner: UNT Libraries Government Documents Department

Jet effects on pressure loading of all-movable horizontal stabilizer

Description: Report presenting an investigation in the 8- by 6-foot supersonic tunnel to determine the effects of a cold exhaust jet on the pressure loadings of an all-movable, 45 degree sweptback horizontal stabilizer located in a region influenced by the jet. Results indicated that at jet pressure ratios of 1 to 9, the exhaust jet did not appreciably affect the pressure loadings of the stabilizer.
Date: June 10, 1954
Creator: Valerino, Alfred S.
Partner: UNT Libraries Government Documents Department

Note on the Scavenge of 6-Inch-Diameter Ram-Jet Exhaust in Mach 3.1, 1- by 1-Foot Supersonic Tunnel

Description: From Summary: "The exhaust of a 6-inch-diameter ram-jet engine mounted in the Lewis 1- by 1-foot, Mach 3.1 supersonic tunnel was scavenged successfully with a 6.6-inch-diameter scoop. Limiting values of exhaust-to-stream static-pressure ratios and scavenge-system total-pressure ratios were determined for complete scavenging of the products of combustion. The scavenge-system operation influenced the engine exhaust-nozzle pressures under conditions of unstable scavenge flow."
Date: February 18, 1955
Creator: Burgess, Warren C., Jr. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Further experiments on the flow and heat transfer in a heated turbulent air jet

Description: "Measurements have been made of the mean-total-head and mean-temperature fields in a round turbulent jet with various initial temperatures. The results show that the jet spreads more rapidly as its density becomes lower than that of the receiving medium, even when the difference is not sufficiently great to cause dynamic-pressure function. Rough analytical considerations have given the same relative spread. The effective "turbulent Prandtl number" for a section of the fully developed jet was found to be equal to the true (laminar) Prandtl number within the accuracy measurement" (p. 859).
Date: August 18, 1947
Creator: Corrsin, Stanley & Uberoi, Mahinder S.
Partner: UNT Libraries Government Documents Department

Contribution to the problem of airfoils spanning a free jet

Description: After a brief discussion of the work done up to now on an unwarped wing of constant chord spanning a free jet, the computation of the circulation and lift distribution for different forms of warped wings spanning rectangular and circular jets was carried out. The computed values are compared with test values and the agreement is found to be good. The effect of placing the wing eccentrically is slight and may be applied as a correction factor to the data obtained for wing placed in middle of jet.
Date: June 1936
Creator: Stüper, J.
Partner: UNT Libraries Government Documents Department

An analysis of buzzing in supersonic ram jets by a modified one-dimensional nonstationary wave theory

Description: From Introduction: "The buzz or pulsation of axially symmetric supersonic inlets having central bodies has been the subject of investigations since Oswatitsch first observed the phenomenon in 1944 (ref.1). This buzzing is essentially an oscillation of the normal shock along the spike of certain diffusers operating at mass flows below design, and this buzz decreases the performance of the propulsion units appreciably (ref.2). This paper continues the analysis of the buzzing cycle by means of a modified one-dimensional approach."
Date: July 1956
Creator: Trimpi, Robert L.
Partner: UNT Libraries Government Documents Department

Investigation of the Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 2.02

Description: "An investigation at a free-stream Mach number of 2.02 was made to determine the effects of a propulsive jet on a wing surface located in the vicinity of a choked convergent nozzle. Static-pressure surveys were made on a flat surface that was located in the vicinity of the propulsive jet. The nozzle was operated over a range of exit pressure ratios at different fixed vertical distances from the flat surface. Within the scope of this investigation, it was found that shock waves, formed in the external flow because of the presence of the propulsive jet, impinged on the flat surface and greatly altered the pressure distribution" (p. 1).
Date: June 23, 1954
Creator: Bressette, Walter E.
Partner: UNT Libraries Government Documents Department

Analysis of heat and compressibility effects in internal flow systems and high-speed tests of a ram-jet system

Description: Report discussing an analysis has been made by the NACA of the effects of heat and compressibility in the flow through the internal systems of aircraft along with equations and charts are developed whereby the flow characteristics at key stations in a typical internal system may be readily obtained.
Date: July 21, 1942
Creator: Becker, John V. & Baals, Donald D.
Partner: UNT Libraries Government Documents Department

Application of the theory of free jets

Description: Based upon Kirchoff's theory of free jets the flow through different screen arrangements of flat plates, as chiefly encountered with turbines in the cavitation zone is defined. It is shown by experiments that these theoretical results are very well representative in most cases of the conditions of discharge from water in air and consequently by cavitation. In addition, the experiments reveal a picture of the discrepancies between the actual flow and the theory of discharge of air in air (of water in water without cavitation). These discrepancies are explained qualitatively by the mingling processes between the jets and the dead air zones.
Date: April 1932
Creator: Betz, A. & Petersohn, E.
Partner: UNT Libraries Government Documents Department

Spreading characteristics of a jet expanding from choked nozzles at Mach 1.91

Description: Total-temperature surveys are presented to determine the gross spreading characteristics of jets expanding from axisymmetric convergent and convergent-divergent nozzles in a supersonic stream. The jet spreading was found to be less with stream flow than previously observed in quiescent air.
Date: December 1956
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies

Description: From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
Date: September 24, 1956
Creator: Henry, Beverly Z., Jr. & Cahn, Maurice S.
Partner: UNT Libraries Government Documents Department

Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air

Description: "Investigations have been conducted to determine by means of total-pressure surveys the boundaries of single and twin jets discharging through convergent nozzles into quiescent air. The jet boundaries for the region from the nozzle outlets to a station 6 nozzle diameters downstream are presented for nozzle pressure ratios ranging from 2.5 t o 16.0 and for twin-Jet nozzle center-line spacings ranging from 1.42 to 2.50 nozzle diameters. The effects of these parameters on the interaction of twin Jets are discussed" (p. 1).
Date: August 9, 1950
Creator: Rousso, Morris D. & Kochendorfer, Fred D.
Partner: UNT Libraries Government Documents Department

Analysis and Experimental Observation of Pressure Losses in Ram-Jet Combustion Chambers

Description: From Introduction: "Some experimental data on flame-holder pressure losses have been presented (reference 1 to 4). A theoretical analysis that assume a sudden enlargement of flow area was made at the NACA Lewis laboratory to determine the effect of flame-holder open area and combustion-chamber-inlet Mach number on the pressure losses across flame holders. The results of this analysis were then compared with experimental data obtained with several different flame-holder designs."
Date: November 4, 1949
Creator: Sterbentz, William H.
Partner: UNT Libraries Government Documents Department

An airfoil spanning an open jet

Description: From Summary: "The first part of the report treats of the theory involved. The second part describes the experiments performed for the purpose of proving the theory."
Date: September 1933
Creator: Stüper, J.
Partner: UNT Libraries Government Documents Department

Analysis and Construction of Design Charts for Turbines with Downstream Stators

Description: From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some details and is therefore not included herein."
Date: November 18, 1954
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Partner: UNT Libraries Government Documents Department

Boundaries of supersonic axisymmetric free jets

Description: Report presenting calculations by the method of characteristics of 2960 boundaries of supersonic axisymmetric free jets exhausting from conically divergent nozzles into still air. The calculations covered a range of jet Mach numbers, a ratio of specific heats of the jet, divergence angles of the nozzle, and jet static-pressure ratios. Results regarding the effect of increasing the static pressure ratio, the simulation of one jet boundary by another, and interpolation and extrapolation of calculated boundaries are provided.
Date: October 5, 1956
Creator: Love, Eugene S.; Woodling, Mildred J. & Lee, Louise P.
Partner: UNT Libraries Government Documents Department

Experimental investigation of effects of primary jet flow and secondary flow through a zero-length ejector on base and boattail pressures of a body of revolution at free-stream Mach numbers of 1.62, 1.93, and 2.41

Description: An investigation was made at free-stream Mach numbers of 1.62, 1.93, and 2.41 to determine the effects of a primary jet and secondary air flow on the base pressure and pressures acting over the boattailsurface of a body of revolution for two secondary discharge areas. The Mach numbers of the primary nozzles were 1 and 3.23 with the secondary mass flow being varied from 0 to 10 percent of the primary mass flow. The ratio of jet stagnation temperature to tunnel stagnation temperature was about 0.96. The Reynolds number range of the investigation was from 2.1 x 10(6) to 2.9 x 10(6)based on body length. All testing was conducted with a turbulent boundary layer along the model. This report presents results obtained with zero-length ejector and covers jet static-pressure ratios from the jet-off condition to a maximum of about 128 for the sonic nozzle and to a maximum of about 9 for the supersonic nozzle.
Date: December 6, 1954
Creator: O'Donnell, Robert M. & McDearmon, Russell W.
Partner: UNT Libraries Government Documents Department

The dijet mass spectrum at D-Zero

Description: We present preliminary results from an analysis of jet data collected during the 1994-95 Tevatron Collider run with an integrated luminosity of 93 pb{sup -1}. Measurements of dijet mass spectra in {anti p}p collisions at {radical}s = 1.8 TeV are compared to next-to-leading order QCD calculations.
Date: November 1, 1997
Creator: Abbott, B.
Partner: UNT Libraries Government Documents Department

Spectrums and diffusion in a round turbulent jet

Description: "In a round turbulent jet at room temperature, measurement of the shear correlation coefficient as a function of frequency (through bandpass filters) has given a rather direct verification of Kolmogoroff's local-isotropy hypothesis. One-dimensional power spectrums of velocity and temperature fluctuations, measured in unheated and heated jets, respectively, have been contrasted. Under the same conditions, the two corresponding transverse correlation functions have been measured and compared" (p. 1).
Date: July 1950
Creator: Corrsin, Stanley & Uberoi, Mahinder S.
Partner: UNT Libraries Government Documents Department

Investigation at Mach number 1.91 of spreading characteristics of jet expanding from choked nozzles

Description: It is demonstrated that the temperature profiles of jets expanding into a supersonic stream are considerably smaller than the temperature profiles of jets expanding into quiescent air. The effect on the wake of varying afterbody geometry is shown to be small. The gross spreading characteristics of jets expanding from convergent and convergent-divergent nozzles in the base of a body of revolution with various boattail configurations at a Mach number of 1.91 are presented.
Date: January 11, 1952
Creator: Rousso, Morris D. & Baughman, L. Eugene
Partner: UNT Libraries Government Documents Department

Investigation of Flow in an Axially Symmetrical Heated Jet of Air

Description: The work done under this contract falls essentially into two parts: the first part was the design and construction of the equipment and the running of preliminary tests on the 3-inch jet, carried out by Mr. Carl Thiele in 1940; the second part consisting in the measurement in the 1-inch jet flow in an axially symmetrical heated jet of air.
Date: December 1943
Creator: Corrsin, Stanley
Partner: UNT Libraries Government Documents Department

An investigation of a method for obtaining hydrodynamic data at very high speeds with a free water jet

Description: Report presenting information regarding the feasibility of using a rectangular free water jet to obtain hydrodynamic data at very high speeds. Total-head pressure distributions in the jet and experimental hydrodynamic lift data is provided and compared to data obtained in water tank testing. The data obtained indicates that it is feasible to use a free water jet for this purpose.
Date: June 14, 1954
Creator: Weinflash, Bernard & McGehee, John R.
Partner: UNT Libraries Government Documents Department