Download or read book An Experimental Investigation Using a Normal Jet Plume Simulator to Determine Jet Plume Effects on a Long Slender Rocket Configuration at Mach Numbers from 0 2 to 1 5 written by James H Henderson and published by . This book was released on 1977 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted at the AEDC 16-foot Transonic Wind Tunnel to determine longitudinal stability characteristics of a long slender rocket configuration with simulated jet plume. The effect of jet plume on rocket aerodynamics is given over an angle of attack range from -11 to 11 degrees at Mach numbers from 0.2 to 1.5. Plume simulator chamber pressure varied from 0 to 600 psia. Individual cruciform fin aerodynamic loads are also shown over the same ranges. (Author).
Download or read book A Summary of Jet Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0 2 to 2 3 written by George Batiuk and published by . This book was released on 1976 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report summarizes the studies made to date by the Army Missile Command on the effects of the rocket jet plume on the Stability characteristics of a body of revolution with various fin configurations and at various fin positions on the body. The Mach numbers ranged from 0.2 to 2.3. A normal jet plume simulator was used to obtain the desired plume effects. This report concerns itself with those tests conducted on a 5-in. diameter, 52-in. long model, with a 3 caliber tangent ogive nose.
Download or read book Investigation of Jet Plume Effects on the Longitudinal Stability Characteristics of a Body of Revolution with Various Fin Configurations at Mach Numbers from 0 2 to 2 3 written by James H. Henderson and published by . This book was released on 1976 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were conducted on a body of revolution with various fin configurations to investigate jet plume effects on missile longitudinal stability. A series of cold air normal jets located downstream of the base were utilized to simulate the jet plume. Fins of various planform geometry were tested at a forward longitudinal location only. The angle of attack range was -4 to 11 degrees at Mach numbers of from 0.2 to 2.3. The test was run at the Arnold Engineering Development Center Transonic (16T) and Supersonic (16S) wind tunnels and was designated AEDC SF172/TF360. (Author).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of the Effectiveness of Several Devices in Simulating a Rocket Plume at Free Stream Mach Numbers 0 9 to 1 2 written by James Robert Burt (Jr.) and published by . This book was released on 1971 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effectiveness of several devices in simulating the effects of a rocket plume on the flow field of a typical missile in the transonic Mach number range was investigated. Two plume-shaped solid bodies and three step-type plume simulators were tested. The effects on model pressure distribution of small angle of attack and plume-simulator position were investigated. The analysis showed that all the plume simulators tested can give approximately the same model afterbody pressure distribution at transonic Mach numbers and small angles of attack as an actual rocket plume. (Author).
Download or read book An Investigation of Jet Plume Effects on the Stability Characteristics of a Body of Revolution in Conjunction with Fins of Various Geometry and Longitudinal Positions at Transonic Speeds sting mounted Model with Normal Jet Plume Simulator written by James H Henderson and published by . This book was released on 1975 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt: The main purpose of the report is to discuss some known available transonic flow approximate treatments and their applicabilities, including their limitations. This may suggest the possible future improvement of efforts in this renewed field. (Author).
Download or read book Government Reports Annual Index written by and published by . This book was released on 1982 with total page 1018 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Experimental Investigation of Jet Plume Simulation with Solid Circular Cylinders written by David Earl Reubush and published by . This book was released on 1974 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Jet Pluming on the Static Stability of Five Rocket Models at Mach Numbers of 4 5 and 6 and Static Pressure Ratios Up to 26 000 written by William F. Hinson and published by . This book was released on 1967 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Axisymmetric and Normal Air Jet Plumes and Solid Plume on Cylindrical Afterbody Pressure Distributions at Mach Numbers from 1 65 to 2 50 written by Peter F. Covell and published by . This book was released on 1982 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Experiments on the Effects of Jet Plumes on Pressure Distribution Over a Cylindrical Afterbody at Transonic Speeds written by Joseph P. Nenni and published by . This book was released on 1980 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of the present investigation was to obtain experimentally, the effects of various jet plume parameters on afterbody pressure distributions and to partially validate the Korst modeling procedure. Analysis of the experimental results and supplemental calculations made by the method of characteristics show that the approximate theory used by Korst, gives a good estimate of the plume shape for nozzle exist Mach number of 2.0 and below. For nozzle exit Mach numbers much in excess of 2.0, it appears desirable to include the effect of the nozzle wall boundary layer on plume shape. In addition, afterbody pressure distributions produced by a series of nozzles designed to produce the same plume shape, but with different values of the plume pliability parameter, have been compared with results from a solid plume simulator. In general, the solid plume simulator produces results that agree with the nozzles with the higher values of the plume pliability parameter at zero degrees angle of attack. The correlation deteriorates significantly, however, at five degrees angle of attack. Also, afterbody pressure distributions from model tests on the ZAP rocket motor are presented for future correlation with prototype results. (Author).
Download or read book Effects of Axisymmetric and Normal Air Jet Plumes and Solid Plume on Cylindrical Afterbody Pressure Distributions at Mach Numbers from 1 65 To 2 50 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-14 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel investigation of the interference effects of axisymmetric nozzle air plumes, a solid plume, and normal air jet plumes on the afterbody pressure distributions and base pressures of a cylindrical afterbody model was conducted at Mach numbers from 1.65 to 2.50. The axisymmetric nozzles, which varied in exit lip Mach number from 1.7 to 2.7, and the normal air jet nozzle were tested at jet pressure ratios from 1 (jet off) to 615. The tests were conducted at an angle of attack of 0 deg and a Reynolds number per meter of 6.56 million. The results of the investigation show that the solid plume induces greater interference effects than those induced by the axisymmetric nozzle plumes at the selected underexpanded design conditions. A thrust coefficient parameter based on nozzle lip conditons was found to correlate the afterbody disturbance distance and the base pressure between the different axisymmetric nozzles. The normal air jet plume and the solid plume induce afterbody disturbance distances similar to those induced by the axisymmetric air plumes when base pressure is held constant. Covell, P. F. Langley Research Center NASA-TP-2005, L-14883, NAS 1.60:2005 RTOP 505-43-23-02...
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1968-05 with total page 1468 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Approach to Experimental Investigation of Jet Plume Effects on Missile Aerodynamics written by and published by . This book was released on 1982 with total page 87 pages. Available in PDF, EPUB and Kindle. Book excerpt: An approach to modeling a rocket's plume effects based on the theory of Korst is presented. To implement the modeling scheme an interactive Fortran program was developed which designs model nozzles that produce geometrically simular plumes with simular base flow characteristics as prototype nozzles but use are or some other medium instead of a propellant. Included are the modeling theory, experimental results and the Fortran program with a sample case.
Download or read book An Investigation for Modeling Jet Plume Effects on Missile Aerodynamics written by and published by . This book was released on 1982 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an investigation of concepts for modeling jet plume effects on missile aerodynamics tend to confirm the concepts proposed by Korst. Comparisons were made of afterbody pressure distributions influenced by plumes of the same shape but with different plume Mach numbers and with a solid plume. These comparisons indicate that increasing effect becoming more pronounced with increasing freestream Mach number. The solid plume has the greatest effect on afterbody pressures with the effect increasing considerably at Mach numbers of 1.25 and higher. (Author).
Download or read book Investigation of Solid Plume Simulation Criteria to Produce Flight Plume Effects on Multibody Configuration in Wind Tunnel Tests written by Alonzo L. Frost and published by . This book was released on 1986 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Jet Billowing on Stability of Missile type Bodies at Mach 3 85 written by Reino J. Salmi and published by . This book was released on 1960 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
