| Experimental Studies on the Effects of Thermal Bumps in the Flow-Field around a Flat Plate using a Hypersonic Wind Tunnel |
Jul 2012 |
109 pages |
| Authors:
Konstantinos Kontis; MANCHESTER UNIV (UNITED KINGDOM) SCHOOL OF MECHANICAL AEROSPACE AND CIVIL ENGINEERING
|
 | This report presents investigations performed on the hypersonic flow-field over a flat plate with and without thermal induced bump in the University of Manchester hypersonic blowdown wind tunnel HSST at Mach no. 5.0 and free-stream Reynolds no. 6.2x106 to 11.6x106 per metre. Experiments were conducted with air as the test gas. The report consists of two parts: The first part deals with the experiments using a microheater coil of 16mm ... |
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| Background-Oriented Schlieren Pattern Optimization |
Dec 2011 |
102 pages |
| Authors:
Jeffery E Hartberger; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| This paper describes a test series to investigate background patterns used for the Background-Oriented Schlieren field density measurement technique. Several varying background patterns were substituted under similar fluid density conditions to visualize and isolate the effects of patterns in the background images. A qualitative comparison was completed of the flow visualization results of each background pattern to categorize background conditions that improved the flow visualization image. Changes in background patterns ... |
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| Photogrammetric Measurement of Recession Rates of Low Temperature Ablators Subjected to High Speed Flow |
JUN 2011 |
290 pages |
| Authors:
David W. Callaway; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH GRADUATE SCHOOL OF ENGINEERING AND MANAGEMENT
|
| This research advances a technique to simulate high temperature/high speed effects in a high speed/low temperature environment and to capture recession of the test article in three-dimensions. A method of fabricating dry ice test articles was developed, and the AFIT Mach 3 pressure-vacuum wind tunnel was used in combination with the dry ice test articles to collect three-dimensional ablation data for models of different shapes at stagnation pressures ranging from ... |
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| Estimation of Time Dependent Properties from Surface Pressure in Open Cavities |
Feb-2008 |
90 pages |
| Authors:
Louis Cattafesta; Lawrence Ukeiley; Terry Song; George Shumway; FLORIDA UNIV GAINESVILLE
|
| The intense fluctuating pressures observed in open cavities are extremely detrimental hence the ability to control the flow to minimize them is an important challenge. Many open loop methodologies have proven effective at this for single operating conditions, however they often are detrimental at off design conditions. Closed loop flow control is applicable over a range of flow conditions and is the thrust of many current and past studies. However ... |
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| Independent Stage Control of a Cascade Injector (Postprint) |
OCT 2006 |
17 pages |
| Authors:
H. L. Meicenheimer; E. J. Gutmark; M. R. Gruber; D. R. Eklund; C. D. Carter; K.-Y. Hsu; CINCINNATI UNIV OH DEPT OF AEROSPACE ENGINEERING
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| An experimental investigation of a cascade injector was completed. The objective of this investigation was to determine whether the number of active stages in the cascade injector could be used to control penetration and mixing characteristics. The injector was tested at two overexpanded injection conditions in a Mach 3 crossflow. Shadowgraph and schlieren imaging, Mie scattering, Planar Laser Induced Fluorescence, and pressure profiling were the diagnostic techniques used to reveal ... |
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| Wind Tunnel Study of Interference Effects Relating to Aft Supersonic Ejection of a Store |
DEC 2005 |
118 pages |
| Authors:
Timothy P. Jung; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| An investigation into the issues surrounding the release of a store into a supersonic wake was conducted. A 10-degree half-angle cone was used to model the carrier vehicle as well as the store. The store was 42% than the vehicle. The experiments were conducted at a freestream Mach number of 2.93 and at zero degrees angle of attack. This study analyzed the effects of a support or strut mounted under ... |
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| Cold Flow Testing of a Modified Subscale Model Exhaust System for a Space Based Laser |
JUN 2004 |
64 pages |
| Authors:
David B. Jarrett; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH DEPT OF AERONAUTICS AND ASTRONAUTICS
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| The aim of this research was a continued study of gas-dynamic phenomena that occurred in a set of stacked nozzles as reported by Captains Ian Bautista in 2003 and Scott Bergren in 2002. The arrangement of the stacked nozzles was a modified version of a 1/5th scale-model of one quadrant of the conceptual Space Based Laser Integrated Flight Experiment (SBL IFX) gas dynamic laser. Rather than cylindrical rings of nozzles, ... |
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| Flow Around an Object Projected from a Cavity into a Supersonic Freestream |
MAR 2004 |
90 pages |
| Authors:
Scott T. Bjorge; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
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| The pressure and flow field of a supersonic flow over a cavity, with and without a store, was the focus of this experiment. One cavity geometry (length to depth ratio 3.6) was studied; the freestream Mach number and the placement of the store relative to the cavity floor were varied. The pressure spectra on the cavity floor were markedly different between Mach numbers of 1.8 and 2.9. The Mach 1.8 ... |
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| Medical Ultrasound Technology Research and Development at the University of Washington Center for Industrial and Medical Ultrasound |
02 OCT 2003 |
18 pages |
| Authors:
Lawrence A. Crum; UNIV OF WASHINGTON SEATTLE APPLIED PHYSICS LAB
|
| This grant provided support to expand the scientific program and infrastructure at the University of Washington's Center for Industrial and Medical Ultrasound (CIMU). The many disparate facilities and technical capabilities available to CIMU staff and students were integrated and enhanced to provide a world-class, advanced research center for bioengineering development and graduate education in high-intensity, focused ultrasound (HIFU). This included leveraging of overall research in understanding of acoustic hemostasis and ... |
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| Parallel Volume Rendering Algorithms for Computational Flow Imaging |
23 AUG 2002 |
7 pages |
| Authors:
Yingchuan Wu; Jialing Le; Anzhi He; RUSSIAN ACADEMY OF SCIENCES NOVOSIBIRSK INST OF THEORETICAL AND APPLIED MECHANICS
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| Computational flow imaging (CFI) uses theoretical predictions of the interaction and transmission of optical waves through theoretical flowfield to generate digital pictures that simulate real observations, but visualizing three-dimensional unstructured data from aerodynamics calculations is challenging because the associated meshes are typically larger in size and irregular in both shape and resolution. The goal of this research is to develop a fast, efficient parallel volume rendering algorithm of computational flow ... |
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| Experimental Studies of High-Speed Separated Flows |
MAR 2002 |
489 pages |
| Authors:
J. C. Dutton; W. Grafton; Lillian B. Williams; ILLINOIS UNIV AT URBANA DEPT OF MECHANICAL AND INDUSTRIAL ENGINEERING
|
| This final report describes the results of a four-year research effort that performed experimental studies in the general area of high. speed separated flows. The motivation for this research effort was to investigate in detail high-speed base flows that are similar in nature to those occurring for missiles and projectiles, so that they can be better understood, predicted, and controlled. The research program consisted of two inter-related tasks: (1) planar ... |
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| Fabrication and Cold-Flow Testing of Subscale Space-Based Laser Geometry |
MAR 2002 |
106 pages |
| Authors:
Scott E. Bergren; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT
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| The objectives of this research were to build a facility that could simulate the expected fluid flow properties in the conceptual Space Based Laser Integrated Flight Experiment (SBL IFX) gas dynamic laser using cold-flow, and to investigate the performance of the model. A 1/5th scale model was fabricated and mated to a blow-down/vacuum wind tunnel. Using rapid data acquisition and schlieren photography the diffuser was determined to initially produce similar ... |
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| Plasma Influence on Characteristics of Aerodynamic Friction and Separation Lines Location |
SEP 2000 |
105 pages |
| Authors:
Serguei Leonov; RUSSIAN ACADEMY OF SCIENCES MOSCOW INST OF HIGH TEMPERATURES
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| This report results from a contract tasking Moscow Technical Company Institute of High Temperature RAS as follows: The contractor will analyze experimental plasma data already obtained on different aerodynamic shapes and produce an experiment at plate model. Three types of surface discharges will be tested in this work: HF multi-streamer discharge, micro hollow cathode discharge and glide surface discharge. The project objectives are 1) analysis of ... |
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| Background Oriented Schlieren Demonstrations |
2000 |
37 pages |
| Authors:
H. Richard; M. Raffel; DEUTSCHES ZENTRUM FUR LUFT-UND RAUMFAHRT EV GOETTINGEN (GERMANY)
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| In this project report we present the application of a novel schlieren technique for two different tests. The optical method is referred to as "Background Oriented Schlieren" (BOS) in the following. Additionally the differences between BOS and an extension of it, the reference-free stereoscopic arrangement (BOSS in the following), will be discussed. Experimental studies have been carried out to investigate a supersonic jet in an anechoic chamber of NASA Langley ... |
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| Experimental Studies of Laminar, Transitional, and Turbulent Hypersonic Flows Over Elliptic Cones at Angles of Attack |
JAN 98 |
58 pages |
| Authors:
Michael S. Holden; CALSPAN UB RESEARCH CENTER BUFFALO NY
|
| An experimental study has been performed to examine the three- dimensional characteristics of laminar, transitional and turbulent flow over an elliptic cone lifting body configuration. The experimental studies were performed at Mach numbers between 8 and 12 at Reynolds numbers, based on model length from 5 x 10(exp 5) to 5 x 10(exp 6). Detailed measurements of the distribution of heating and pressure were made along the leading edges and ... |
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| Experimental Study on Supersonic and Hypersonic Flows Around Models withOn-Board Plasma Generators |
1998 |
71 pages |
| Authors:
Mikhail Kogan; TSENTRAL'NYI AERO-GIDRODINAMICHE'SKII INST MOSCOW (RUSSIA)
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| In this report, the results of experiments on the contract SPC-97- 4042 in the wind tunnel T-113 of TsAGI at Mach number M = 4 and static pressure equal 29 torr are presented. The tests were carried out with three types of axisymmetical models. Two of them were equipped by plasma generators and had the different form of the nose part. In front of the bluntness, these ... |
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| Experimental Investigation of the Influence of Molecular Weight on Mixing and Penetration in Supersonic Dissimilar Gaseous Injection into a Supersonic Cross-Flow |
DEC 97 |
53 pages |
| Authors:
Troy A. Giese; AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
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| In pursuit of a more efficient and effective fuel-air mixing for a SCRAMjet combustor, this study investigated relative near field effects of molecular weight on mixing and penetration of different gaseous injection into a supersonic (M=2.9) cross flow. Helium and argon gas were chosen as injectants because of the large differences in molecular weights. Also, mixing enhancement was observed by injecting the traverse gas jet parallel to the compression face ... |
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| Shock Tube Studies of Ram Accelerator Phenomena |
16 OCT 1997 |
7 pages |
| Authors:
R. K. Hanson; STANFORD UNIV CA DEPT OF MECHANICAL ENGINEERING
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| This research was aimed at developing an improved understanding of hypersonic exothermic flows through the application of modern experimental methods and finite-rate-chemistry flowfield modeling. The emphasis has been on providing fundamental data, of flowfield structure and combustion ignition times, which are relevant to the ongoing development of the ram accelerator concept. Work in flow imaging and modeling utilized the Stanford expansion tube with a combined OH PLIF and schlieren imaging ... |
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| Numerical and Experimental Investigation of the Flowfield Near a Wrap- Around Fin |
MAR 97 |
150 pages |
| Authors:
Carl P. Tilmann; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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| A wall-mounted semi-cylindrical model fitted with a single wrap- around fin (WAF) has been investigated both numerically and experimentally, with the objective of characterizing the mean and turbulent flowfield in the vicinity of the fin. Numerical and experimental results are used to determine the nature of the flowfield and quantify the effects of fin curvature on the character of the flow near WAFs. This research has been motivated by the ... |
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| (AASERT-93) Turbulent Reacting Flows at High Speed |
30 SEP 96 |
22 pages |
| Authors:
Alexander J. Smits; Frederick L. Dryer; J. Fielding; PRINCETON UNIV NJ
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| A pilot-scale supersonic combustion tunnel was designed and constructed to operate with initial stagnation temperatures up to 900 K and static pressure and stagnation temperature ranges of 0.01-0.1 atm. and 290-900 K, respectively, in the test chamber without vitiation of the nitrogen/oxygen gas supply. Through the addition of hydrogen in the upstream settling chamber, the effective operating stagnation temperature in the test section was extended to 1100 K. The tunnel ... |
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| Research Instrumentation for Fluid Dynamic Mechanisms and Interactions within Separated Flows |
31 JAN 96 |
4 pages |
| Authors:
J. C. Dutton; ILLINOIS UNIV AT URBANA DEPT OF MECHANICAL AND INDUSTRIAL ENGINEERING
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| This report describes the equipment purchased under ARO Research Instrumentation Grant No. DAAH04-94-G-0386. This equipment has been used to support the ARO research program entitled, 'Fluid Dynamic Mechanisms and Interactions with Separated Flows' (ARO Grant No. DAAH04-93-G-0226). In particular, instrumentation has been purchased to obtain measurements and flow visualizations using schlieren and shadowgraph photography, laser Doppler velocimetry, particle image velocimetry, and Mie/Rayleigh scattering. The specific pieces of equipment, vendors, and ... |
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| Experimental Investigation of a Supersonic Boundary Layer Including Favorable Pressure Gradient Effects |
19 DEC 95 |
198 pages |
| Authors:
Joel J. Luker; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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| This study used advanced laser Doppler velocimetry techniques to measure the turbulence intensities and Reynolds shear stresses in Mach 2.8 turbulent flat plate and Mach 2.9 favorable pressure gradient (FPG) boundary layers. The FPG was generated using a convex curved wall and had a strength of Beta = 0.1, where Beta is Clauser's equilibrium parameter. The maximum magnitude of the 'extra' strain rates normalized by the main strain rates was ... |
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| Experimental Investigation of Non-Adiabatic Supersonic Slot Injection into a Supersonic Cross-Flow |
19 DEC 95 |
155 pages |
| Authors:
Kelly C. Tucker; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| Turbulence and mean flow measurements were acquired downstream of a normal, supersonic (M=1.6), two-dimensional, slot injection into Mach 3.0 flow (Re/m = 15x10 to the 6th power). Two non-adiabatic cases (Tti/Tt = 1.11 and Tti/ Tt = 0.93) were studied. Multiple overheat anemometry and conventional mean flow analysis, as well as shadowgraph and schlieren photography, were utilized to study the turbulent mixing layer. The mean flow data included the Pitot, ... |
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| Mach 2.9 Investigation Into The Flow Structure In The Vicinity of a Wrap-Around Fin |
DEC 95 |
103 pages |
| Authors:
Richard E. Huffman Jr; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| A ceiling-mounted semi-cylindrical model containing a single wrap- around fin (WAF) was tested in the AFIT Mach 2.9 test facility. Flow visualization using oil- low streaklines, schlieren images and shadowgraph photography revealed a A-shock at the fin-body juncture and the development of an asymmetric bow-shock about the fin. Quantitative measurements were taken with a 100 cone-static pressure probe, a Pitot pressure probe and two cross- wire hot-film probes (u-v and ... |
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| Experimental Investigation of a Supersonic Turbulent Boundary Layer with Adverse Pressure Gradient |
DEC 95 |
145 pages |
| Authors:
Chad S. Hale; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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| Laser Doppler Velocimetry (LDV) measurements were made to quantify the effect of adverse pressure gradient on the compressible turbulent flow structure in a Mach 2.9 boundary layer (Re/m= 1.75 x 10to the 7th power). Measurements included profiles of 2-D mean velocities, turbulence intensities, Reynolds shear stresses, intermittency, flatness and skewness. In addition, mean strain rates were also measured. The boundary layer measurements were acquired for both flat plate and compression ... |
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| Thrust Vector Control of Rectangular Jets using Counterflow |
07 JUL 95 |
135 pages |
| Authors:
A. Krothapalli; D. J. Forliti; FLORIDA STATE UNIV TALLAHASSEE DEPT OF MECHANICAL ENGINEERING
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| This research studied the flow generated by a rectangular convergent- divergent Mach 2 nozzle operated in a free jet and a counterflow thrust vectored configuration. Particle Image Velocimetry was used to obtain 2D velocity fields and total and static pressures were measured. In the free jet configuration, the nozzle was operated at ideal, over, and underexpanded conditions. The growth of shear layers was unaffected by shock cells for mildly off-design ... |
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| A Wind Tunnel Investigation of a Wing-Tip Trailing Vortex |
25 MAY 95 |
284 pages |
| Authors:
Mark A. Engel; William J. Devenport; VIRGINIA POLYTECHNIC INST AND STATE UNIV BLACKSBURG DEPT OF AEROSPACE AND OCE AN ENGINEERING
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| The 3'x2' Subsonic Wind Tunnel was used to study a wing-tip trailing vortex during its development at the wingtip and at 10 chordlengths downstream. The vortex was found to be well developed by 10 chordlengths. Helium bubble flow-visualization was used to study the development of the vortex in the near- tip regions. Hot wire anemometry was used to study the vortex at 10 chordlengths. Two vortices were found in the ... |
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| Analysis of Planar Laser-Induced Fluorescence Images Obtained During Shakedown Testing of the AEDC Impulse Facility |
MAR 95 |
62 pages |
| Authors:
W. M. Ruyten; W. D. Williams; F. L. Heltsley; ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFS TN
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| Following a proof-of-principle demonstration of Planar Laser-Induced Fluorescence (PLIF) in the AEDC Impulse Facility in FY93, a set of four PLIF images was obtained during FY94 runs of the facility. The images were obtained away from the nose region of a spherically blunt cone, using excitation of nitric oxide in the flow. Two laser sheet geometries were employed and two excitation wavelengths were used. A procedure was developed whereby calibration ... |
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| BIAXIAL TESTING OF COMPOSITES - A STUDY OF THE DISK SPECIMEN. |
01 JAN 1995 |
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| Authors:
Paul Cavallaro; Lisa Gee; Nikos Tsangarakis
|
 | Army Research Laboratory : Watertown, Massachusetts |
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| Compressible Turbulence Measurements in a Supersonic Boundary Layer Including Favorable Pressure Gradient Effects |
13 DEC 94 |
115 pages |
| Authors:
Raymond S. Miller; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| The effect of a favorable pressure gradient on the turbulent flow structure in a Mach 2.9 boundary layer (Re/m approx. 1.5 x 10(exp 7)) is investigated experimentally. Conventional flow and hot film measurements of turbulent fluctuation properties have been made upstream of and along an expansion ramp. Upstream measurements were taken in a zero pressure gradient boundary layer 44 cm from the nozzle throat in a 6.35 cm square test ... |
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| An Experimental Study Of Planar Heterogeneous Supersonic Confined Jets |
DEC 94 |
184 pages |
| Authors:
Frederick J. Tanis Jr; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH
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| The effects of varying the exit pressure of a supersonic helium jet exhausting coaxially with two parallel supersonic air streams into a constant area duct were investigated. The method used to evaluate the mass entrainment rate was to measure helium molar concentration profiles and mass flux across the duct using a binary gas probe then calculate the mass entrainment into the helium jet. In order to conduct this study a ... |
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| Expansion Effects on Supersonic Turbulent Boundary Layers |
FEB 94 |
190 pages |
| Authors:
Stephen A. Arnette; Mo Samimy; Gregory S. Elliott; OHIO STATE UNIV COLUMBUS DEPT OF MECHANICAL ENGINEERING
|
| The effects of various expansion regions on the large scale structure of a Mach 3 fully-developed-turbulent boundary layer are investigated. Five cases are studied: 7 deg and 14 deg centered expansions, 7 deg and 14 deg gradual expansions, and the flat plate. Multi-point surface pressure measurements, filtered Rayleigh scattering visualizations, and double-pulse visualizations were employed. Plan view images of the flat plate boundary layer reveal the presence of structures of ... |
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| Noninvasive Spectral Analysis and Beam Mapping of Focused Ultrasound. Part 1 |
JAN 94 |
135 pages |
| Authors:
Walter Mayer; Thomas Neighbors; Herbert Ruf; John Wolf; Qicao Zhu; GEORGETOWN UNIV WASHINGTON DC DEPT OF PHYSICS
|
| This is a report on the noninvasive analysis of ultrasonic fields where nonlinear distort initially sinusoidal sound fields, with the main emphasis being placed on the acousto-optic (schlieren) investigation of line- focused ultrasound propagating in water. Computational models and experimental results are presented as well as some results of phenomena related to reflection and transmission at boundaries of pulsed sound fields. Ultrasound(Focused), Ultrasound(Pulsed), Noninvasive method, Acousto-optics, Nonlinear ultrasonics |
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| Real-Time Adaptive Control of Mixing in a Plane Shear Layer |
14 DEC 93 |
225 pages |
| Authors:
Ari Glezer; Frank H. Champagne; ARIZONA UNIV TUCSON
|
| A control system for the enhancement and regulation of mixing in a nonreactive plane shear layer has been developed in a two-stream closed-return water facility. Mixing of a passive scalar is estimated using a thermal analog in which the two streams have uniform, steady temperatures differing by 3 C. Control is effected via an array of surface heaters flush-mounted on the flow partition and cross-stream temperature distributions are measured with ... |
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| Real-Time Parameter Identification Applied to Flight Simulation. |
APR 1993 |
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| Authors:
L. A. Pineiro; D. J. Biezad; AERONAUTICAL SYSTEMS CENTER WRIGHT-PATTERSON AFB OH
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| In-flight simulations are normally accomplished using model-following control laws which depend on accurate knowledge of the stability derivatives of the host aircraft. Degraded simulation results if the stability derivatives deviate considerably from their presumed values. Gain scheduling is often employed to compensate for plant parameter variations, but this form of open-loop compensation usually requires extensive flight testing for proper fine tuning. An adaptive, fast-sampling control law to compensate for changing ... |
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| REACTION PROCESSING: ROUTE FOR CONTROLLING COMPOSITE INTERFACIAL BEHAVIOR. |
01 JAN 1993 |
|
| Authors:
S. G. Fishman
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| Proceedings of the 6th Japan-U.S. Conference on Composite Materials; Held in Orlando, Florida, Jun 1992; Edited by K. L. Reifsnider; Technomic Publishing Company, Inc. : Lancaster, Pennsylvania |
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| NONLINEAR ANALYSIS OF COMPOSITE STRUCTURES BASED ON A MODERN CONTINUUM MIXTURE THEORY. |
01 JAN 1993 |
|
| Authors:
Andrew C. Hansen
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| Proceedings of the 6th Japan-U.S. Conference on Composite Materials; Held in Orlando, Florida, Jun 1992; Edited by K. L. Reifsnider; Technomic Publishing Company, Inc. : Lancaster, Pennsylvania |
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| COMPARISON OF TWO-DIMENSIONAL CONTINUUM AND LAYERED BEAM FINITE ELEMENT MODELS OF A COMPOSITE NOTCHED TENSILE BAR. |
01 JAN 1993 |
|
| Authors:
Stuart J. Harbert; Harry A. Hogan
|
| Proceedings of the 6th Japan-U.S. Conference on Composite Materials; Held in Orlando, Florida, Jun 1992; Edited by K. L. Reifsnider; Technomic Publishing Company, Inc. : Lancaster, Pennsylvania |
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| THE EFFECT OF BENDING-TWISTING COUPLING ON THE CRITICAL SPEED OF A DRIVESHAFT. |
1993 |
|
| Authors:
Charles W. Bert
|
| Proceedings of the 6th Japan-U.S. Conference on Composite Materials; Held in Orlando, Florida, Jun 1992; Edited by K. L. Reifsnider; Technomic Publishing Company, Inc. : Lancaster, Pennsylvania |
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| Comparison of HOB Curves for 0.5-g NP Charges with Field Test Data and Calculations |
01 JUL 92 |
75 pages |
| Authors:
Heinz Reichenbach; Gunther Scheklinski-Gluck; Allen Kuhl; LOGICON R AND D ASSOCIATES LOS ANGELES CA
|
| Experiments are described on the reflection of spherical blast waves from planar surfaces. The blast waves were created by the detonation of 0.5-g spherical charges of NITROPENTA (NP). The scale of the experiments was about 1/ 1000 per kiloton. Diagnostics included schlieren photography and a high-speed pressure measurement system. A parametric series of height-of-burst (HOB) experiments were conducted over hydrodynamically smooth, rough and porous surfaces. Peak pressure measurements were used ... |
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| A Plume-Induced Boundary Layer Separation Experiment |
30 JUN 92 |
18 pages |
| Authors:
Russell J. Shaw; J. C. Dutton; ILLINOIS UNIV AT URBANA DEPT OF MECHANICAL AND INDUSTRIAL ENGINEERING
|
| The current paper describes an experimental investigation of a PIBLS flowfield produced by the interaction between two nonparallel, supersonic streams in the presence of a finite thickness base. The purpose of the study is to gain a better understanding of., the extent to which the fluid dynamic mechanisms and interactions present in the PIBLS flowfield influence the turbulence properties of the flow. A two-stream, supersonic wind tunnel, incorporating a two-dimensional ... |
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| Reversible Multiphoton Ionization of Gases Observed by a Femtosecond Pump/Probe Schlieren Imaging Technique, |
22 MAY 1992 |
|
| Authors:
J. P. Geindre; P. Audebert; J. C. Gauthier; R. Benattar; A. Mysyrowicz; ECOLE POLYTECHNIQUE PALAISEAU (FRANCE) LAB DE PHYSIQUE DES MILIEUX IONISES
|
| Using femtosecond time-resolved Schlieren imaging, we observe a light-induced reversible plasma-like change of the refractive index of a gas during optical irradiation by 80 fs laser pulses. |
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| Optical Diagnostics in Supersonic Combusting Systems |
APR 92 |
169 pages |
| Authors:
T. E. Parker; M. G. Allen; S. J. Davis; K. Donohue; R. R. Foutter; PHYSICAL SCIENCES INC ANDOVER MA
|
| The development of supersonic combusting ramjet (SCRAMJET) engines requires testing using new, nonintrusive, instrumentation methods in high-speed, high-enthalpy flow facilities. This report describes a test series using a shock tunnel to produce Mach 3.0 flows with stagnation temperatures in excess of 3000 K and an optical diagnostic set specifically tailored for measurements in supersonic high temperature systems. The test facility includes a hydrogen injection capability which makes combustion tests possible ... |
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| A Real Time Interferometry System for Unsteady Flow Measurements |
OCT 91 |
10 pages |
| Authors:
N. J. Brock; M. S. Chandrasekhara; L. W. Carr; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| A simple real-time interferometer system was developed for use in dynamic stall and other unsteady flow research at compressible flow speeds. A conventional schlieren system was modified to operate as a point diffraction interferometer. The implementation of this interferometer is discussed and results of trails with different point diffractors are presented in this paper. The performance of the interferometer under various flow conditions was investigated. Results are presented which show ... |
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| Modification and Experimental Validation of a Combined Optical and Collection Probe for Solid Propellant Exhaust Analysis |
MAR 91 |
89 pages |
| Authors:
Lyle J. Kellman; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| A combined optical and collection particle sizing probe was further developed and utilized for insitu measurements in the exhaust plumes of solid propellant rocket motors. Probe shock-swallowing capabilities were verified using schlieren observations under restricted motor operating conditions. Particle size number distributions obtained optically using a Malvern Mastersizer and from an automated data retrieval system for scanning electron microscope photographs of collected particles were in good agreement when referenced to ... |
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| Preliminary Investigation of the Shock-Boundary Layer Interaction in a Simulated Fan Passage |
MAR 91 |
129 pages |
| Authors:
Christopher C. Collins; NAVAL POSTGRADUATE SCHOOL MONTEREY CA
|
| A two dimensional, two passage simulation of the relative flow through a transonic fan at M = 1.4 was designed with a view to providing an apparatus in which to assess the effectiveness of passive vortex generator techniques in alleviating shock-boundary layer interaction effects. The design of the model and the results of six test runs in the transonic cascade blowdown wind tunnel are described. Schlieren photographs of the shock ... |
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| A Study of the Gas-Phase Chemistry of Solid Propellant Ingredients Using CO2 Laser Heating |
91 |
10 pages |
| Authors:
Thomas A. Litzinger; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
|
| This research program is designed to address the critical need for data on the gas phase chemistry of solid propellants through the development and application of a Microprobe Mass Spectrometer (MPMS) system. The MPMS systems is being used to study the gas-phase chemistry occurring above solid propellant ingredients and actual solid propellants when they are heated and/or ignited by the heat flux from a Carbon dioxide laser. Currently the MPMS ... |
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| A Study of Gas Phase Chemistry of Solid Propellants Using a Microprobe Mass Spectrometer System. Results for RDX, BLX-9, XM-39, M9 and JA-2 |
91 |
20 pages |
| Authors:
Thomas A. Litzinger; PENNSYLVANIA STATE UNIV UNIVERSITY PARK COLL OF ENGINEERING
|
| This research program is designed to address the critical need for data on the gas-phase chemistry of solid propellants through the development and application of a microprobe mass spectrometer (MPMS) system. The MPMS system is being used to study the gas-phase chemistry occurring above solid propellant ingredients and actual solid propellants when they are heated and/or ignited by the heat flux from a CO2 laser. In addition to the MPMS ... |
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| A Study of the Gas Phase Chemistry of Solid Propellants Using a Microprobe Mass Spectrometer (MPMS) System: Preliminary Results for Solid Fuels (HTPB/Zecorez and BAMO/NMMO), Single-Base Propellant (M10) and an RDX-Based Propellant (BLX-9) |
91 |
26 pages |
| Authors:
Thomas A. Litzinger; PENNSYLVANIA STATE UNIV UNIVERSITY PARK
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| Detailed knowledge of the gas-phase reactions which occur during propellant ignition and combustion are required to understand and model these processes. If detailed models were available, modification of propellant formulations for improved combustion behavior could be achieved with much less trial-and-error testing. Furthermore, detailed models could be used to generate simplified kinetics schemes for use in propellant models. The present research program, centers around the development and application of a ... |
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| Effects of Specific Heat Ratio on a Simulated Chemical Laser Cavity Flow |
DEC 90 |
104 pages |
| Authors:
Curt D. Botts; AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
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| Mixing of primary cold flow air and secondary helium to control the ratio of specific heats for the medium flowing through a simulated chemical laser nozzle/lasing cavity was accomplished. The effects of a range of mixture specific heat ratios on flowfield behavior were examined using static pressure ports in the test cavity. Schlieren photography and high speed filming aided description of the flow dynamics. Results indicated that boundary layer effects ... |
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SCHLIEREN PHOTOGRAPHY
