Download or read book Transonic Wind Tunnel Investigation of Thrust Effects on Missile Aerodynamics written by R. J. Dennis and published by . This book was released on 1973 with total page 278 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were conducted on an Army Missile Command (AMC) base drag research missile model in the Calspan Corporation 8-Foot Transonic Wind Tunnel during January of 1973. These tests were conducted in order to determine the effect of jet plumes on the stability characteristics of fin and ringtail afterbody confugurations. Afterbody forces and moments and base pressure were measured at jet thrust levels from zero to 400 pounds. The tests were conducted at Mach numbers from zero to 1.25 and at angles of attack from -5 to +10 degrees. The report presents details of the test program, an outline of the test procedures, and results of the investigation in tabular form.
Download or read book Results of a Transonic Wind Tunnel Investigation of Thrust Effects on the Aerodynamics of Four Longitudinally Supported Ringtail Missile Configurations written by J. H. Henderson and published by . This book was released on 1973 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt: D MISSILES, TUBE LAUNCHEDTransonic wind tunnel tests were conducted on a strut-supported model to determine thrust effects on four longitudinal strut supported ringtail configurations. The configurations were achieved by varying the distance between the nozzle exit plane and the ringtail. Thrust was simulated by cold air and was varied from 0 to 400 pounds. Of primary interest, was the effect of thrust level and longitudinal position of the nozzle exit plane on missile stability. For the thrust levels tested, a favorable effect on longitudinal stability was experienced on the configuration with the nozzle exit plane located at the ringtail leading edge. The test was conducted at the Calspan Corporation's 8 foot Transonic Wind Tunnel at Mach numbers ranging from 0.4 to 1.2. Angles of attack were from -5 degrees to +6 degrees at a sideslip angle of 0 degrees. Thrust, from 0 to 400 pounds, was the only varying parameter. (Author).
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 Results of a Transonic Wind Tunnel Investigation of Trust Effects on the Aerodynamics of the Longbow Missile Configuration written by J. H. Henderson and published by . This book was released on 1973 with total page 81 pages. Available in PDF, EPUB and Kindle. Book excerpt: ERODYNAMICS OF THE Longbow Missile Configuration. Technical rept., Henderson, J. H. ;RD-TR-73-18DA-1-M-262303-A-214*Antiradiation missiles, *Transonic characteristics, *Wind tunnel tests, *Thrust, Wind tunnel models, Bodies of revolution, Fins, Aerodynamic configurations, Air to surface missiles, Jets, Air, Angle of attack, Base pressure, Plumes*LONGBOW missilesTransonic wind tunnel tests were conducted on a strut-mounted model of the LONGBOW missile configuration to determine thrust effects on a body of revolution afterbody with fins located at various longitudinal positions. Thrust was simulated by a cold air axial jet. Base pressure and afterbody forces and moments were measured. The test was conducted at Mach numbers from 0.4 to 1.25 and at angles of attack from -2 degrees to 10 degrees. Jet thrust was varied from 0 to 400 pounds. Reynolds number per foot varied from 0.7 to 1.7 million. (Modified author abstract).
Download or read book Results of Transonic Wind Tunnel Investigations to Determine the Effects of Nozzle Geometry and Jet Plume on the Aerodynamics of a Body of Revolution written by and published by . This book was released on 1972 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic wind tunnel test was conducted by the Army Missile Command, Redstone Arsenal, on a base drag research missile model in the Cornell Aeronautical Laboratory (CAL) 8-Foot Transonic Wind Tunnel during June 1972. The test was conducted to investigate the effects of nozzle geometry on jet plume characteristics at high thrust levels and to study the effects of nozzle geometry on base pressure at low thrust levels. Model external and nozzle internal static pressure measurements were obtained on all nozzles. This report presents details of the test program, an outline of the test procedures and the results of the investigations in plotted form. (Author).
Download or read book Transonic Wind Tunnel Investigation of Thrust Effects on the Longitudinal Stability Characteristics of Several Body Fin Confugurations Sting Mounted Model with Normal Jet Plume Simulator written by J. H. Henderson and published by . This book was released on 1974 with total page 437 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 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 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Wind Tunnel and Full scale Forces on Rocket Sleds written by Daniel J. Krupovage and published by . This book was released on 1967 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt: Vertical quasi-steady state forces on three dual rail rocket sleds, which were predicted using wind tunnel data, are compared with those measured on the Holloman Test Track. A description of the magnitude and character of the oscillatory forces is also presented. This is the first such comparison since the advent of rocket sled testing. Wind tunnel force tests on the three rocket sleds indicated that aerodynamic forces would be of sufficient magnitude to warrant consideration in structural design. The forces measured during the track tests indicated that the aerodynamic contribution was the dominant component to the vertical quasi-steady state force in the supersonic regime. The results of full-scale investigations showed implicitly that when the sleds experienced considerable aerodynamic forces, the wind tunnel data agreed fairly well with the forces measured on the rocket sled. The quasi-steady state vertical forces were predicted, using wind tunnel data, to within 3,000 pounds for loads between 12,000 and 32,000 pounds. (Author).
Download or read book Wind tunnel Studies at Subsonic and Transonic Speeds of a Multiple mission Variable wing Sweep Airplane Configuration written by William J. Alford and published by . This book was released on 1959 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Missile Aerodynamics written by Jack Norman Nielsen and published by AIAA (American Institute of Aeronautics & Astronautics). This book was released on 1988-01-01 with total page 450 pages. Available in PDF, EPUB and Kindle. Book excerpt: The similarities between the airplane and the missile extend beyond their flying capabilities, and at higher operational speeds, the configuration distinctions become even less apparent. " Missile Aerodynamics," a classic now available from AIAA and Nielsen Engineering and Research, Inc., combines the best of missile and airplane aerodynamics, drawing extensively from numerous technical papers to present a rational and unified account of the principles behind missile projection. Evaluate the missile versus the airplane in a multitude of areas, from longitudinal acceleration, wing loading, roll and dynamic stability, guidance and navigation, and more. J.N. Nielsen covers every aspect of missile aerodynamics, from the classification of missiles and basic formulas to innovative aerodynamic controls. In one reliable reference, readers will find hundreds of schematics, equations, and tables with practical applications in missile design and engineering. Originally published by Nielsen Engineering and Research, Inc.
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings Volume I written by and published by . This book was released on 1973 with total page 670 pages. Available in PDF, EPUB and Kindle. Book excerpt: Transonic wind tunnel tests were performed in an Calspan Corporation (formerly Cornell Aeronautical Laboratory) Eight-Foot Transonic Wind Tunnel on a missile model with canard wings. The tests were conducted during the end of April and the beginning of May, 1973. Two distinctly different investigations were made. The effect of canard wing positions, canard - tail angular orientation, canard size, model roll angle, and nose shape, were investigated during the Aerodynamic Test Phase. The use of canard wings for roll attitude control was also investigated during this phase. The effect of different jet plumes on the aerodynamic model loads were studied during the Thrust Effect Phase. A normal jet plume simulator was used and the effects of model tail position, planform, and orientation were investigated. The report presents details of the test program and the results in tabular form.
Download or read book Wind tunnel Investigation at Mach Numbers from 0 40 to 1 20 of the Static Aerodynamic and Control Characteristics of a Model of a Nonlifting Reeintry Capsule in Combination with a Rocket Booster written by Albin O. Pearson and published by . This book was released on 1960 with total page 74 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Transonic Wind Tunnel Investigation of the Static Longitudinal Aerodynamic Characteristics of Five Nose Cones Designed for Supersonic Impact written by John P. Jr Mugler and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
