Download or read book Transonic Wind Tunnel Tests of a Base Drag Research Missile Model written by B. F. Gorin and published by . This book was released on 1970 with total page 583 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted in order to obtain data describing the effects of various simulated rocket exhaust plumes on the model's external flow field. Data describing the flow in the nozzle exit plane and in the model boundary layer were also obtained. Model external static pressure measurements were made and Schlieren, shadowgraph and tuft photographs were taken. The tests were conducted at Mach numbers from 0.000 to 1.200 at angles of attack from -2 to +2 degrees. The report presents details of the test program, an outline of the test procedure and the results of the investigation in tabular form. (Author).
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 Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper and published by . This book was released on 1973 with total page 674 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report is Volume 2 of a three volume series. Tables of aerodynamic test data are given, including balance cavity and base pressure coefficients, axial force for aerodynamic and thrust phases, canard position, and force and moment coefficients for a series of runs.
Download or read book Drag Measurements from Different Wind Tunnels written by and published by . This book was released on 1966 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 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 Technical Abstract Bulletin written by and published by . This book was released on with total page 850 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Investigation of Drag Repeatability in Half Model Testing in the ARA Transonic Wind Tunnel written by I. F. Burns and published by . This book was released on 1993 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Transonic Wind Tunnel Tests of A 1 15 Scale Model of the TALOS 6cl Missile written by Michael E. McDonald and published by . This book was released on 1961 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests of a 1/15-scale model of the TALOS 6cl missile were performed in the TMB 7- by 10-Foot Transonic Wind Tunnel for a Mach number range of 0.7 to 1.17, at angles of attack of -4 to 10, and roll angles of 0 and -45. The investigation included evaluation of the effects of ram-air bleed at the base of the second stage and the longitudinal stability and control effectiveness of the missile. The data are presented without analysis. (Author).
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 Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper 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 NASA Technical Memorandum written by and published by . This book was released on 1981 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic Wind Tunnel Tests on a Missile Model with Canard Wings written by R. E. DE Kuyper and published by . This book was released on 1973 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Volume 3 of a three volume report tabulates aerodynamic and thrust test data on a wind tunnel model of a guided missile with canard wings. Included are tail fin force and moment coefficients.
Download or read book U S Government Research Reports written by and published by . This book was released on 1962 with total page 614 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Transonic and Supersonic Wind Tunnel Test of the Action Hypervelocity Test Missile Volume 2 Drag Characteristics written by William D. Washington and published by . This book was released on 1974 with total page 381 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two wind tunnel tests were conducted at AEDC and BRL to define the stability characteristics of the ACTION hypervelocity test missile. The AEDC test investigated the transonic launch-coast phase of flight while the BRL test investigated the supersonic boost-sustain phase. The basic flight configuration was tested plus configuration which consisted of changes in the nose, canards, canard position, and flared angle. Mach numbers investigated ranged from 0.3 to 4.5 over an angle of attack range of -4 to +4 degrees at 0 degrees sideslip. The test was designated BRL 955/AEDC 289. This report is presented in two volumes. Volume 2 contains drag characteristics data. (Author).
