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 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 Investigation of Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Transonic Speeds written by R. E. DE Kuyper and published by . This book was released on 1974 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic wind tunnel test was performed in the Calspan Corporation 8-Foot Transonic Wind Tunnel on a missile model with tail fins in the presence of a simulated jet plume. The test was conducted during February, 1974. The purpose of the test was to establish a correlation between the thrust level and missile longitudinal stability, and to assess the effectiveness of locating stabilizing fins forward of the model base as a means of alleviating adverse plume effects. This was the second series of tests performed with this model at Calspan. The results of the earlier test, which also included a canard effectiveness study, were previously reported. The test was conducted over a Mach number range from 0.40 to 1.25 at a condition corresponding to a wind-off static pressure of 0.5 atmospheres. Model angle of attack was varied from -4 to 12 degrees.
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 Effects of Body and Fin Deflections on the Aerodynamic Characteristics in Pitch of a 0 065 scale Model of a Four stage Rocket Configuration at Mach Numbers of 1 41 and 1 82 written by Ross B. Robinson and published by . This book was released on 1959 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1977 with total page 560 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1977 with total page 1078 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government reports annual index written by and published by . This book was released on 1978 with total page 1268 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Investigation of Thrust Effects on the Longitudinal Stability Characteristics of Several Body fin Configurations written by James H. Henderson and published by . This book was released on 1974 with total page 872 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were conducted on a sting-mounted model to determine thrust effects on longitudinal stability characteristics of several body-fin combinations. The plume was simulated by cold air ejected from a series of sonic jets normal to the missile axis. One fin configuration was tested at several longitudinal positions. Adverse plume effects on stability were reduced by location of fins a distance forward of the base. The test was conducted at the Calspan Corporations' 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.25. Angles of attack ranged from -4 degrees to 12 degrees. Data were also obtained at roll angles of 22.5 degrees and 45 degrees for one configuration.
Download or read book Some Effects of Fin Plan Form on the Static Stability of Fin body Combinations at Mach Number 4 06 written by Edward F. Ulmann and published by . This book was released on 1952 with total page 28 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 A Wind tunnel Investigation of Effects of Noise Bluntness Face Shape and Afterbody Length on the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2 37 2 98 and 3 90 written by and published by . This book was released on 1960 with total page 48 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:
Download or read book A Wind tunnel Investigation of the Aerodynamic Characteristics of Bodies of Revolution at Mach Numbers of 2 37 2 98 and 3 90 at Angles of Attack to 90 Deg written by and published by . This book was released on 1960 with total page 40 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 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 Effects of Several Nose and Vertical fin Modifications on the Low angle of attack Static Stability of a Winged Reentry Vehicle at Mach Numbers of 9 6 in Air and 17 8 in Helium written by and published by . This book was released on 1961 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Performance Stability and Control Investigation at Mach Numbers from 0 4 to 0 9 of a Model of the Swallow with Outer Wing Panels Swept 25 Degree with and Without Power Simulation written by and published by . This book was released on 1960 with total page 72 pages. Available in PDF, EPUB and Kindle. Book excerpt:
