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1دورية أكاديمية
المؤلفون: Rubin, Donald
المساهمون: ARMY MISSILE RESEARCH DEVELOPMENT AND ENGINEERING LAB REDSTONE ARSENAL AL AEROBALLISTICS DIRECTORATE
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Guided Missile Warheads and Fuzes, GUIDED MISSILE MODELS, AERODYNAMIC DRAG, ANGLE OF ATTACK, BLEED SYSTEMS, BOUNDARY LAYER CONTROL, DRAG REDUCTION, EXPERIMENTAL DATA, FINS, FLOW RATE, GUIDED MISSILE COMPONENTS, INJECTION, MASS FLOW, NITROGEN, NOSE CONES, OGIVES, STABILIZATION SYSTEMS, SUPERSONIC CHARACTERISTICS, SUPERSONIC WIND TUNNELS, TURBULENT BOUNDARY LAYER, WIND TUNNEL TESTS, FLUID INJECTION, PE62303A
الوصف: To determine general effects of fluid injection into a turbulent boundary layer on missile drag and stabilizing forces at angle of attack, an exploratory investigation was made at Mach 1.63 and 2.2. The test model was a body of revolution 10-cal long with a 3-cal tangent ogive nose and stabilizing fins. The mass injection was simulated by nitrogen and injected into the boundary layer from a porous section just aft of the nose body junction. The porous section was varied in length from 0.5 to 1.5 cal. Angle of attack range varied from -3.5 deg to +19 deg.
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2دورية أكاديمية
المؤلفون: Cahill, David M
المساهمون: ARNOLD ENGINEERING DEVELOPMENT CENTER ARNOLD AFB TN
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Guided Missile Dynam, Config & Cntrl Surfaces, Surface-launched Guided Missiles, INSTRUMENTATION, PRESSURE DISTRIBUTION, SURFACE TO SURFACE MISSILES, Force(Mechanics), Moments, Payload, Payload analyses, Mach number, Angle of attack, Minuteman, Minuteman 3 missiles, Supersonic characteristics, Minuteman instrumented payload delivery system, Nose cones, Transonic characteristics, Wind tunnel models, Model tests, Guided missile models
الوصف: Wind tunnel tests were conducted in the Arnold Engineering Development Center (AEDC) Aerodynamic Wind Tunnel (4T) on a 0.06-scale model of the Minuteman Instrumented Payload Delivery System (MIPDS). Pressure distributions and force and moment data were obtained over a Mach number range from 0.5 to 1.3, at angles of attack from -6 to 24 deg, and at angles of roll from -180 to 165 deg. ; Prepared in cooperation with ARO, Inc., Tullahoma, TN, Rept. no. ARO-PWT-TR-76-73.
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3دورية أكاديمية
المؤلفون: Morrison, A. M., Holmes, J. E., Lawrence, W. R.
المساهمون: NAVAL SURFACE WEAPONS CENTER WHITE OAK LAB SILVER SPRING MD
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Guided Missile Dynam, Config & Cntrl Surfaces, PITCH(MOTION), DAMPING, NOSE CONES, COMPUTER PROGRAMS, ANGLE OF ATTACK, SUPERSONIC CHARACTERISTICS, DEGREES OF FREEDOM, EQUATIONS OF MOTION, STABILITY, ONE DEGREE OF FREEDOM
الوصف: A series of one-degree-of-freedom dynamic wind tunnel measurements were made for a standard Supersonic Tunnel Association ten degree cone with varying bluntnesses of .25, .1, .0167, and .07. Variations of the stability coefficients with angle-of-attack, bluntness, Reynolds number, and Mach number are obtained including Mach 18 data points for which no previous data existed. An explanation of reported difference between measured dynamic stability as obtained from ballistic range and wind tunnel techniques is offered. The equations of motion, data reduction techniques and experimental methods are also developed.
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4دورية أكاديمية
المساهمون: AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Aerodynamics, Guided Missiles, GUIDED MISSILES, AERODYNAMIC CHARACTERISTICS, EXPERIMENTAL DATA, SLENDER BODIES, YAW, LOADS(FORCES), WAKE, MACH NUMBER, REYNOLDS NUMBER, NOSE CONES, TRANSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, SUBSONIC CHARACTERISTICS, WIND TUNNEL TESTS, VORTICES, ANGLE OF ATTACK, VORTEX SHEDDING, FLOW FIELDS, MX MISSILES, PE62201F, WUAFWAL24040701
الوصف: A large body of wind tunnel data was generated by tests of a smooth missile model with several interchangeable nose parts. The tests were conducted at subsonic through supersonic speeds at angles of attack from 0 to 180 degrees. They were part of the FDL and SAMSO technology studies which preceded design of the MX missile. Measurements of both surface pressures and total forces and moments were made at a variety of Mach numbers and Reynolds number combinations. This data was supplemented with wake flow-field measurements of the impact pressure and flow direction at angles of attack where maximum induced side force was expected to occur. A review of the literature for subsonic and transonic aerodynamic characteristics of bodies of revolution was conducted. A comprehensive discussion is provided of the important variables of the high angle of attack flow phenomena. The test data provided insight into the effect of several variables that had not been adequately treated in the past. The high angle of attack data was analyzed to deduce the vortex shedding location, the vortex strength, and the vortex paths in the wake. Discrete vortex theory was examined as a method which could be modified, based on experimental data, and used to predict the aerodynamic characteristics of missiles to greater accuracy. An alternate approach to developing a prediction method was explored by means of a correlation of the surface pressure data. ; Prepared in collaboration with Rutgers, The State University of New Jersey.
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5دورية أكاديمية
المؤلفون: Cottrell,Charles J, Chapman,Gary T
المساهمون: AIR FORCE ARMAMENT LAB EGLIN AFB FL
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Fluid Mechanics, TURBULENT BOUNDARY LAYER, FREE STREAM, FLOW SEPARATION, LAMINAR BOUNDARY LAYER, COMPUTATIONS, PARAMETERS, COMPARISON, MOMENTS, VARIATIONS, CYLINDRICAL BODIES, LIMITATIONS, PARABOLAS, MACH NUMBER, FLUID DYNAMICS, SUPERSONIC CHARACTERISTICS, NAVIER STOKES EQUATIONS, PRESSURE DISTRIBUTION, SKIN FRICTION, NOSE CONES, FLARED AFTERBODIES, PE61102F, WUAFATL2307E125
الوصف: A Parabolized Navier-Stokes (PNS) code's capability to predict the onset of laminar and turbulent boundary layer separation, forces, moments, and pressure distributions was investigated. Predictions of incipient separation show good agreement with experimental results. Force and moment calculations were found to agree favorably with experimental data for a wide range of geometries for mach numbers from 2 to 4 with turbulent boundary layers. Limited comparison of pressure distribution data also showed good agreement. Skin friction and Stanton number calculations are presented to indicate the code's capability to calculate this information and hence, provide a complete data base for attached flow conditions. The sensitivity of these calculations to smoothing and marching parameter variations was examined and found to be acceptable for most design work. The code was found to be suitable to complement or reduce wind tunnel experimentation for the design of this class of configuration with regard to accuracy, cost and usability. Keywords: Computational fluid dynamics; Separated flow; Supersonic freestream aerodynamic prediction.
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6دورية أكاديمية
المؤلفون: Devan,Leroy
المساهمون: NAVAL SURFACE WEAPONS CENTER DAHLGREN VA
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Aerodynamics, COMPUTERIZED SIMULATION, AERODYNAMIC CHARACTERISTICS, COMPUTATIONS, PARAMETERS, TAIL ASSEMBLIES, SHOCK WAVES, ANGLE OF ATTACK, COEFFICIENTS, PARTIAL DIFFERENTIAL EQUATIONS, MACH NUMBER, NUMERICAL METHODS AND PROCEDURES, DRAG, SUPERSONIC CHARACTERISTICS, STATICS, INVISCID FLOW, TACTICAL WEAPONS, BODIES, LAGRANGIAN FUNCTIONS, TRANSONIC CHARACTERISTICS, NOSE CONES, BODIES OF REVOLUTION, AS214, PE61153N
الوصف: An existing methodology for predicting static and aerodynamic coefficients was extended to higher angles of attack and Mach numbers. Improvements in existing computational methods were also made. The theory is applicable to bodies of revolution with one or two, piecewise similar-cross section lifting surfaces (2 or 4 number). The original methodology was applicable to a Mach number of 3 and to an angle of attack of 15 deg. The capability for dynamic derivative prediction for small angles was extended and improved to Mach numbers of the order 6, above which real gas effects and much stronger viscous coupling are important. Static aerodynamic prediction capability at small angles of attack was extended and improved to M sub infinity = 6, and empirical code developed for the Army by G. Aiello of the Martin-Marietta Corp. (Orlando) was adapted for prediction of static aerodynamics at higher angles of attack for a limited configurational envelope. The Martin-Marietta code predicts body-tail aerodynamics for arbitrary roll orientation and angles of attack to 45 deg for 0.8 M sub infinity 3. Body-alone and wing-along(in the presence of the body) components can be computer to alpha = 180 deg and for 0.8 M sub infinity 3. New individual computational methods are evaluated by comparison with other computational methods and experimental data. The resulting extended computer program was segmented in order to conserve storage locations. Computational times depending on Mach number, configuration, and program option range from under a second to a minute per Mach number on the CDC 6700 computer.
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7دورية أكاديمية
المؤلفون: Sturek,Walter B, Mylin,Donald C, Bush,Clarence C
المساهمون: BALLISTIC RESEARCH LABS ABERDEEN PROVING GROUND MD
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Aerodynamics, Fluid Mechanics, SLENDER BODIES, AERODYNAMIC STABILITY, SUPERSONIC CHARACTERISTICS, SPIN STABILIZATION, COMPUTERIZED SIMULATION, TURBULENT FLOW, FINITE DIFFERENCE THEORY, CYLINDRICAL BODIES, AERODYNAMIC DRAG, SPINNING(MOTION), OGIVES, INVISCID FLOW, EXTERIOR BALLISTICS, BOUNDARY LAYER FLOW, THREE DIMENSIONAL FLOW, NOSE CONES, MAGNUS EFFECT
الوصف: Recent trends in projectile design have led to shapes with greater length and more slender ogives. Unexpected flight stability problems have been encountered due to decreased aerodynamic stability of these new shapes. Clearly, conventional aerodynamic predictive capabilities were not adequate. In an effort to avoid these problems in the future, the Ballistic Research Laboratory has been developing advanced numerical computational techniques for computing projectile aerodynamic characteristics to improve shell design technology.
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8دورية أكاديمية
المؤلفون: Wolny,William
المساهمون: LUNDY TECHNICAL CENTER POMPANO BEACH FL
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Pilotless Aircraft, Mfg & Industrial Eng & Control of Product Sys, Countermeasures, Pyrotechnics, CHAFF DISPENSERS, COUNTERMEASURES, DISPENSERS, FLARES, MAINTENANCE, CONTROL SYSTEMS, PAYLOAD, TAIL ASSEMBLIES, CYCLES, INSTALLATION, WEIGHT, EXTERNAL STORES, OPERATION, DRONES, SUPERSONIC CHARACTERISTICS, CHECKOUT PROCEDURES, NOSE CONES, ELECTRIC DETONATORS, SEQUENCE SWITCHES, AN/ALE-44
الوصف: The objective of this report is to document all pertinent data, methods and procedures to install, operate and maintain the AN/ALE-44 countermeasure dispensing system. The report includes system characteristics, loading and check-out procedures. (Author)
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9دورية أكاديمية
المساهمون: FOREIGN TECHNOLOGY DIV WRIGHT-PATTERSON AFB OH
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Fluid Mechanics, Guided Missile Reentry Vehicles, Aircraft, TRANSONIC AIRFOILS, AERODYNAMIC FORCES, NOSE CONES, SHOCK WAVES, CHINA, CHINESE LANGUAGE, TRANSLATIONS, BLUNT BODIES, INTERFERENCE, FINITE ELEMENT ANALYSIS, BLAST WAVES, SUPERSONIC CHARACTERISTICS, FLOW FIELDS
الوصف: Contents: Effect of Nose Bluntness on Twin Wave Interference; Application of Finite Element Method to Transonic Airfoils - A Preliminary Steady Subcritical Calculation. (Chinese Translations; China) ; Edited trans. of Ke Daxue Xuebao (China) v16 n1 p66-77 Mar 86.
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10دورية أكاديمية
المؤلفون: Cowperthwaite, R. L., McEwan, Michael D.
المساهمون: MCDONNELL AIRCRAFT CO ST LOUIS MO
المصدر: DTIC AND NTIS
مصطلحات موضوعية: Computer Programming and Software, Guided Missiles, Thermodynamics, (*REENTRY VEHICLES, COMPUTER PROGRAMS), ABLATION), SIMULATION, ATMOSPHERE ENTRY, AERODYNAMIC HEATING, CONVECTION(HEAT TRANSFER), CONICAL BODIES, NOSE CONES, COMPUTER PROGRAMMING, SUPERSONIC CHARACTERISTICS, FLOW CHARTING, MATERIALS, MATHEMATICAL PREDICTION, BOUNDARY LAYER TRANSITION, REYNOLDS NUMBER, TEMPERATURE, ENTHALPY, VELOCITY, TWO DIMENSIONAL FLOW, FORTRAN, LOSSES, MASS, envir, info
الوصف: The program described herein is a simple method for predicting the ablation performance of a reentry vehicle. The program calculates the heating rates and total mass loss for a conical vehicle during a hypothetical reentry. This report discusses the related theory and program functions, and presents a sample case for further clarity. The program is written in FORTRAN IV computer language. This report is one of six volumes providing users' manuals for a series of computer programs developed for the Air Force Weapons Laboratory. (Author)
