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).
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1977 with total page 1068 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Fin flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1 61 and 2 20 written by Clyde Hayes and published by . This book was released on 1965 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of Plume Effects on the Stability Characteristics of a Body of Revolution with Various Fin Configurations at Transonic Speeds written by R. E. DE Kuyper and published by . This book was released on 1974 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt: A transonic wind tunnel test was performed in the Calspan Corporation 8-Foot Transonic Wind Tunnel on a missile model with tail fins in the presence of a simulated jet plume. The test was conducted during February, 1974. The purpose of the test was to establish a correlation between the thrust level and missile longitudinal stability, and to assess the effectiveness of locating stabilizing fins forward of the model base as a means of alleviating adverse plume effects. This was the second series of tests performed with this model at Calspan. The results of the earlier test, which also included a canard effectiveness study, were previously reported. The test was conducted over a Mach number range from 0.40 to 1.25 at a condition corresponding to a wind-off static pressure of 0.5 atmospheres. Model angle of attack was varied from -4 to 12 degrees.
Download or read book Some Effects of Flare and Nose Shape on the Damping in pitch Characteristics of a Blunt Nosed Flare stabilized Body at Transonic Mach Numbers written by James C. Monfort and published by . This book was released on 1962 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Systematic Study of the Static Stability Characteristics of a Series of Afterbody Flare Fin and Boattail Configurations at Mach Numbers from 1 57 to 2 87 written by and published by . This book was released on 1959 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Effect of Flare and Ramp Angle on the Upstream Influence of Laminar and Transitional Reattaching Flows from Mach 3 to 7 written by J. Don Gray and published by . This book was released on 1967 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of laminar- and transitional-flow separation induced by flares and ramps of different angles was conducted at Mach numbers 3, 5, and 7 over a broad Reynolds number range. Surface pressure distributions, schlieren and shadowgraph pictures, and the oil film technique were used to determine the effect of transition during flow reattachment on the scale of laminar separation. It is concluded that because transition was always triggered prematurely by the reattachment pressure gradient, small flow deflections (theta
Download or read book An Investigation of the Static and Dynamic Aerodynamic Characteristics of a Series of Blunt nosed Cylinder flare Models at Mach Numbers from 0 65 to 2 20 written by David E. Jr Reese and published by . This book was released on 1960 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation of the Drag of Blunt nosed Bodies of Revolution in Free Flight at Mach Numbers from 0 6 to 2 3 written by Harvey A. Wallskog and published by . This book was released on 1953 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effects of Forebody Strakes and Mach Number on Overall Aerodynamic Characteristics of Configuration with 55 Deg Cropped Delta Wing written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 174 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind tunnel data base was established for the effects of chine-like forebody strakes and Mach number on the longitudinal and lateral-directional characteristics of a generalized 55 degree cropped delta wing-fuselage-centerline vertical tail configuration. The testing was conducted in the 7- by 10-Foot Transonic Tunnel at the David Taylor Research Center at free-stream Mach numbers of 0.40 to 1.10 and Reynolds numbers based on the wing mean aerodynamic chord of 1.60 x 10(exp 6) to 2.59 x 10(exp 6). The best matrix included angles of attack from 0 degree to a maximum of 28 degree, angles of sidesip of 0, +5, and -5 degrees, and wing leading-edge flat deflection angles of 0 and 30 degrees. Key flow phenomena at subsonic and transonic conditions were identified by measuring off-body flow visualization with a laser screen technique. These phenomena included coexisting and interacting vortex flows and shock waves, vortex breakdown, vortex flow interactions with the vertical tail, and vortices induced by flow separation from the hinge line of the deflected wing flap. The flow mechanisms were correlated with the longitudinal and lateral-directional aerodynamic data trends. Erickson, Gary E. and Rogers, Lawrence W. Langley Research Center AERODYNAMIC CHARACTERISTICS; DELTA WINGS; FLOW CHARACTERISTICS; FOREBODIES; LATERAL STABILITY; LONGITUDINAL STABILITY; MACH NUMBER; STRAKES; WIND TUNNEL TESTS; AIRFOIL PROFILES; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; CHORDS (GEOMETRY); FLOW VISUALIZATION; SHOCK WAVES; VORTEX BREAKDOWN; VORTICES; WING FLAPS...
Download or read book Effect Opf Fin flare Combinations on the Aerodynamic Characteristics of a Body at Mach Numbers 1 61 and 2 20 written by Clyde Hayes and published by . This book was released on 1965 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Pressure Distribution on a Cone cylinder flare Body at Mach 14 in the Presence of Flow Separation written by Eric G. Friberg and published by . This book was released on 1968 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Surface pressure data are presented for a cone-cylinder-flare body with 20 deg and 40 deg flare angles at a nominal freestream Mach number of fourteen. Separation of the flow due to the adverse pressure gradient induced by the flare was found in both cases. Appreciable extent of separation existed in the 40 deg flare case, while for the 20 deg flare separation was less severe. A correlation formula using the viscous interaction parameter is shown to be valid for a wide range of Mach numbers and model geometries. (Author).
Download or read book A Pressure distribution Investigation of the Aerodynamic Characteristics of a Body of Revolution in the Vicinity of a Reflection Plane at Mach Numbers of 1 41 and 2 01 written by John P. Gapcynski and published by . This book was released on 1955 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: The changes in the aerodynamic characteristics of a body of revolution with a fineness ratio of 8 have been determined at Mach numbers of 1.41 and 2.01, a Reynolds number, based on body length, of 4,540,000, and angles of incidence of 0 degrees and plus or minus 3 degrees as the position of the body is varied with respect to a reflection plane. The data are compared with theoretical results.
Download or read book Exploratory Tests of the Effects of Jet Plumes on the Flow Over Cone cylinder flare Bodies written by Ralph A. Falanga and published by . This book was released on 1962 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Schlieren photographs were taken of the flow over cone-cylinder-flare bodies to study the extent of boundary-layer separation due to the presence of rocket jet plumes. Tests were made of three cone-cylinder-flare configurations in the Langley 11-inch hypersonic tunnel at a Mach number of 9.65 and in the Langley Unitary Plan wind tunnel at a Mach number of 4.65 with two additional configurations. The stream Reynolds number varied from approximately 317,000 to 582,000 based on model length. The conical flares had half-angles of 7 or 13 degrees and contained one of two test nozzles with a design Mach number of 3.72 or 4.53.
Download or read book An Experimental Study of Plume Effects on Lifting Re entry Vehicles written by John R. Rausch and published by . This book was released on 1971 with total page 340 pages. Available in PDF, EPUB and Kindle. Book excerpt: Tests were conducted at Mach numbers of 6, 8, and 10 on a representative lifting body entry vehicle and a Mach number of 10 on a flat plate using heated air and other gases to simulate rocket exhaust plumes. Extensive flow separation resulting from the plumes was observed on both configurations during the test program and the most powerful parameters which affected plume induced separation included: model shape, angle of attack, Reynolds number, nozzle expansion ratio, nozzle total pressure, and nozzle gas temperature and specific heat. The flat plate model showed much less flow separation than the delta planform at similar test conditions, however, serious problems in control effectiveness were indicated on both models for the aft mounted elevon. The data did not correlate well with existing semi-empirical correlations developed for control surface induced separation and plume shape. New semi-empirical correlations were developed for predicting plume shape in a region of plume induced separation and for predicting the pressure and the extent of the separated region.
Download or read book Experimental Study of Effects of Geometric Variables on Performance of Conical Rocket Engine Exhaust Nozzles written by Harry E. Bloomer and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Twenty Second Symposium on Naval Hydrodynamics written by National Research Council and published by National Academies Press. This book was released on 2000-03-02 with total page 1039 pages. Available in PDF, EPUB and Kindle. Book excerpt: The Twenty-Second Symposium on Naval Hydrodynamics was held in Washington, D.C., from August 9-14, 1998. It coincided with the 100th anniversary of the David Taylor Model Basin. This international symposium was organized jointly by the Office of Naval Research (Mechanics and Energy Conversion S&T Division), the National Research Council (Naval Studies Board), and the Naval Surface Warfare Center, Carderock Division (David Taylor Model Basin). This biennial symposium promotes the technical exchange of naval research developments of common interest to all the countries of the world. The forum encourages both formal and informal discussion of the presented papers, and the occasion provides an opportunity for direct communication between international peers.
