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 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 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 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 Government Reports Announcements written by and published by . This book was released on 1974 with total page 952 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 1974 with total page 900 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Results of Transonic Wind Tunnel Investigation to Determine the Effects of Nozzle Geomatry and Jet Plume on the Aerodynamics of a Body of Revolution Technical Report written by James H. Henderson and published by . This book was released on 1972 with total page 235 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Index written by and published by . This book was released on 1975 with total page 908 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at Mach Numbers from 1 90 to 2 86 of a Canard controlled Missile with Ram air jet Spoiler Roll Control written by A. B. Blair and published by . This book was released on 1978 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Government Reports Announcements Index written by and published by . This book was released on 1974 with total page 204 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind Tunnel Investigation of Aerodynamic Loads on Weapons Separated from Carriage Under the Wing of a Tactical Fighter Aircraft at Supersonic Speeds written by J. C. Donaldson and published by . This book was released on 1973 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Download or read book Wind Tunnel Investigation of Vortex Flows on F a 18 Configuration at Subsonic Through Transonic Speed written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-23 with total page 170 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel experiment was conducted in the David Taylor Research Center 7- by 10-Foot Transonic Tunnel of the wing leading-edge extension (LEX) and forebody vortex flows at subsonic and transonic speeds about a 0.06-scale model of the F/A-18. The primary goal was to improve the understanding and control of the vortical flows, including the phenomena of vortex breakdown and vortex interactions with the vertical tails. Laser vapor screen flow visualizations, LEX, and forebody surface static pressures, and six-component forces and moments were obtained at angles of attack of 10 to 50 degrees, free-stream Mach numbers of 0.20 to 0.90, and Reynolds numbers based on the wing mean aerodynamic chord of 0.96 x 10(exp 6) to 1.75 x 10(exp 6). The wind tunnel results were correlated with in-flight flow visualizations and handling qualities trends obtained by NASA using an F-18 High-Alpha Research Vehicle (HARV) and by the Navy and McDonnell Douglas on F-18 aircraft with LEX fences added to improve the vertical tail buffet environment. Key issues that were addressed include the sensitivity of the vortical flows to the Reynolds number and Mach number; the reduced vertical tail excitation, and the corresponding flow mechanism, in the presence of the LEX fence; the repeatability of data obtained during high angle-of-attack wind tunnel testing of F-18 models; the effects of particle seeding for flow visualization on the quantitative model measurements; and the interpretation of off-body flow visualizations obtained using different illumination and particle seeding techniques. Erickson, Gary E. Glenn Research Center F-18 AIRCRAFT; FOREBODIES; INTERACTIONAL AERODYNAMICS; LEADING EDGES; VORTEX BREAKDOWN; VORTICES; WIND TUNNEL TESTS; WINGS; ANGLE OF ATTACK; BUFFETING; FLOW VISUALIZATION; MACH NUMBER; REYNOLDS NUMBER; STABILIZERS (FLUID DYNAMICS); SUBSONIC SPEED; TAIL ASSEMBLIES; TRANSONIC SPEED; TRANSONIC WIND TUNNELS...
Download or read book Wind Tunnel Investigation of Vortex Flows on F A 18 Configuration at Subsonic Through Transonic Speeds written by Gary E. Erickson and published by . This book was released on 1991 with total page 172 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 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 Transonic Wind tunnel Investigation of the Fin Loads of a 1 8 scale Model Simulating the First Stage of the Scout Research Vehicle written by Thomas C. Kelly and published by . This book was released on 1961 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wind tunnel Investigation at a Mach Number of 2 91 of Stability and Control Characteristics of Three Lifting Reentry Configurations at Angles of Attack Up to 90 written by John E. Grimaud and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
