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Effects Of Simulated Rocket Jet Exhaust On Stability And Control Of A Research Type Airplane Configuration At Mach Number Of 686
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Book Synopsis Effects of Simulated Rocket-jet Exhaust on Stability and Control of a Research-type Airplane Configuration at Mach Number of 6.86 by : David E. Fetterman
Download or read book Effects of Simulated Rocket-jet Exhaust on Stability and Control of a Research-type Airplane Configuration at Mach Number of 6.86 written by David E. Fetterman and published by . This book was released on 1959 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Simulated Rocket-jet Exhaust on Stability and Control of a Research-type Airplane Configuration at a Mach Number of 6.86 by : David E. Jr Fetterman
Download or read book Effects of Simulated Rocket-jet Exhaust on Stability and Control of a Research-type Airplane Configuration at a Mach Number of 6.86 written by David E. Jr Fetterman and published by . This book was released on 1959 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Free-flight Investigation of the Effects of Simulated Sonic Turbojet Exhaust on the Drag of a Boattail Body with Various Jet Sizes from Mach Number 0.87 to 1.50 by : Ralph A. Falanga
Download or read book A Free-flight Investigation of the Effects of Simulated Sonic Turbojet Exhaust on the Drag of a Boattail Body with Various Jet Sizes from Mach Number 0.87 to 1.50 written by Ralph A. Falanga and published by . This book was released on 1955 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: Three 7.5 degree boattail bodies of revolution with varying base-annulus areas and jet sizes provided with simulated-turbojet-exhaust rocket motors were flight-tested to determine the jet interference effects on drag over a Mach number range from approximately 0.87 to 1.5. The results indicated that in the transonic and low-supersonic speed range the jet caused positive pressure increments on the base and boattail which appreciably reduced the configuration drag from the power-off condition. At the high supersonic speeds, the jet caused positive pressure increments only on the base and resulted in a smaller reduction in body drag from power-off conditions.
Book Synopsis Investigation of Engine-exhaust-airframe Interference on a Cruise Vehicle at Mach 6 by : James M. Cubbage
Download or read book Investigation of Engine-exhaust-airframe Interference on a Cruise Vehicle at Mach 6 written by James M. Cubbage and published by . This book was released on 1971 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.
Book Synopsis Rocket-model Investigation of Lateral Stability Characteristics and Power Effects of a Jet-engine Airplane Configuration with Tail Boom at Mach Numbers from 1.15 to 1.37 by : T. Bradley Curry
Download or read book Rocket-model Investigation of Lateral Stability Characteristics and Power Effects of a Jet-engine Airplane Configuration with Tail Boom at Mach Numbers from 1.15 to 1.37 written by T. Bradley Curry and published by . This book was released on 1961 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : George Batiuk
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.
Book Synopsis 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 by : James H. Henderson
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).
Book Synopsis An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 by : Calvin Wayne Dahlke
Download or read book An Investigation of Flow and Stability Characteristics for a Body of Revolution with Fins and Flare in Presence of Plume Induced Separation at Mach Numbers 0.7 to 1.4 written by Calvin Wayne Dahlke and published by . This book was released on 1977 with total page 200 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a wind tunnel test, simulating rocket motor exhaust jet effects on missile aerodynamic at Mach numbers of 0.7 to 1.4 are presented. A normal jet plume simulator was used to induce afterbody boundary layer separation. Flow visualization techniques including both shadowgraph and oil flow photographs were taken. The primary emphasis for this report is the force and moment measurements taken on twelve configurations including: five tail fin configurations; body alone; three forward fin configurations; body flare combination; and two combinations of forward fins/strakes with tail fins. All force and moment coefficients are presented in plotted form. One configuration is shown with ground plane interference simulation. (Author).
Book Synopsis Design and Evaluation of a Turbojet-exhaust Simulator with a Solid-propellant Rocket Motor for Free-flight Research by : Abraham Leiss
Download or read book Design and Evaluation of a Turbojet-exhaust Simulator with a Solid-propellant Rocket Motor for Free-flight Research written by Abraham Leiss and published by . This book was released on 1957 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1982 with total page 1282 pages. Available in PDF, EPUB and Kindle. Book excerpt: Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Book Synopsis 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 by : James H Henderson
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).
Book Synopsis Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range by : C. E. Robinson
Download or read book Exhaust Plume Temperature Effects on Nozzle Afterbody Performance Over the Transonic Mach Number Range written by C. E. Robinson and published by . This book was released on 1974 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of an experimental and analytical research investigation on nozzle/afterbody drag are presented. Experimental afterbody (and boattail) drag coefficients and pressure distributions are discussed for an isolated, strut-mounted nozzle/afterbody model for the Mach number range from 0.6 to 1.5. Some data are also given for free-stream unit Reynolds numbers from one million to approximately four million per foot. The experimental data were obtained for the basic model with an air-cooled and a water-cooled Ethylene/air combustor to provide hot-jet duplication as well as cold-jet simulation. The temperature of the nozzle exhaust gas was varied from 530R (burner-off) to approximately 2500R for several nozzle pressure ratios from jet-off to those corresponding to a moderately under-expanded exhaust plum. The initial series of experiments was conducted with the air-cooled combustors, and the effect of jet temperature on afterbody drag was somewhat masked by the effects of the secondary airflow from the cooling air. The general trend, however, shows a decreasing afterbody drag with increasing exhaust gas temperature and with decreasing secondary airflow at a fixed nozzle pressure ratio. (Modified author abstract).
Author :United States. National Aeronautics and Space Administration Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :966 pages Book Rating :4.F/5 ( download)
Book Synopsis NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration Scientific and Technical Information Division and published by . This book was released on 1970 with total page 966 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :964 pages Book Rating :4.E/5 ( download)
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports by : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Download or read book A Selected Listing of NASA Scientific and Technical Reports written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1970 with total page 964 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :United States. National Aeronautics and Space Administration. Scientific and Technical Information Division Publisher : ISBN 13 : Total Pages :956 pages Book Rating :4.:/5 (317 download)
Book Synopsis NASA Scientific and Technical Reports and Publications for 1969 - A Selected Listing by : United States. National Aeronautics and Space Administration. Scientific and Technical Information Division
Download or read book NASA Scientific and Technical Reports and Publications for 1969 - A Selected Listing written by United States. National Aeronautics and Space Administration. Scientific and Technical Information Division and published by . This book was released on 1970 with total page 956 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers by : L. L. Galigher
Download or read book Evaluation of Boattail Geometry and Exhaust Plume Temperature Effects on Nozzle Afterbody Drag at Transonic Mach Numbers written by L. L. Galigher and published by . This book was released on 1976 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental program was conducted to investigate the interaction effects which occur between the nozzle exhaust flow and the external flow field associated with isolated nozzle afterbody configurations at transonic Mach numbers. Pressure data were obtained from three afterbody geometries with boattail angles of 10, 15, and 25 deg at Mach numbers from 0.6 to 1.5 at zero angles of attack and sideslip. Cold (High-pressure air) and hot (Air/ethylene combustion) jet test techniques were used to simulate and duplicate, respectively, the nozzle exhaust flow for a sonic jet installation. Nozzle exhaust temperature was varied from 540 to approximately 2,900 R. The most significant results pertain to those effects on boattail pressure drag caused by exhaust plume temperature and flow asymmetry (Model support strut induced). The differences obtained in boattail pressure drag between the cold jet simulation and hot jet duplication results were significant at nozzle pressure ratios representative for turbofan and turbojet engines at subsonic Mach numbers. Adjusting the cold jet nozzle pressure ratio to correct for changes in the exhaust plume specific heat ratio with temperature did not account for the differences observed. Flow asymmetry effects were Mach number and nozzle pressure ratio dependent and increased in severity as the boattail angle was increased.
