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1 edition of An investigation of the transonic pressure drag coefficient for axi-symmetric bodies found in the catalog.

An investigation of the transonic pressure drag coefficient for axi-symmetric bodies

Eddy Priyono

An investigation of the transonic pressure drag coefficient for axi-symmetric bodies

by Eddy Priyono

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Published by Naval Postgraduate School, Available from National Technical Information Service in Monterey, Calif, Springfield, Va .
Written in English


About the Edition

This thesis investigates the pressure drag coefficient in the transonic regime over an axi-symmetric body, with a set of unique contour surfaces developed in a previous thesis. The contour surfaces were obtained by an exact solution of the small perturbation transonic equation, using the guidelines and tools developed at NPS. In this work, Computational Fluid Dynamics (CFD) was not only used to compute the afterbody contour surface, but also to investigate a conical afterbody and complete bodies, which are composed of an arbitrary forebody (ellipsoid) and a variable afterbody (contour and conical). Euler as well as Navier-Stokes flow-solvers were applied to the geometries of interest, giving Mach-number contours for viscous and inviscid flow, pressure drag coefficient magnitude, and depicting shock wave location. On the basis of these results, it can be verified that our contour surface afterbodies will decrease by 15% the peak of the pressure drag coefficient (C sub d) versus Mach number curves in the transonic regime. These results can be used to design low pressure drag surfaces for such as missiles, projectiles and aircraft engine nacelles

Edition Notes

Statement Eddy Priyono
The Physical Object
Pagination85 p. ;
Number of Pages85
ID Numbers
Open LibraryOL25454466M

Critical Pressure Coefficient PRESSURE COEFFIENT WHERE THE LOCAL MACH NUMBER IS 1. Critical Pressure Coefficient “Slender Bodies of Minimum Wave Drag, #MINDRAG. Title: Microsoft PowerPoint - Topic 22 - Transonic Aerodynamics - Author: devenpor Created Date: 4/28/ PM. Nguyen, Van-Tu, Ha, Cong-Tu, and Park, Warn-Gyu. "Multiphase Flow Simulation of Water-Entry and -Exit of Axisymmetric Bodies." Proceedings of the ASME International Mechanical Engineering Congress and Exposition. Volume 7A: Fluids Engineering Systems and Technologies. San Diego, California, USA. November 15–21, V07AT08A ASME.

Transonic shockwave motion over a NACA aerofoil undergoing linear acceleration and deceleration was reported by [10] for magnitudes of 5g and 10g. Pressure coefficient was shown to vary significantly between the unsteady and steady state cases for low transonic Mach numbers ( The pressure coefficient is approximately. () Equation () is a valid approximation for small perturbations in subsonic or supersonic flow. For 2-D flows over planar bodies it is sufficient to retain only the first term in () and we use the expression. () For 3-D flows over slender approximately axisymmetric bodies we.

  Viscious Drag Computation for Axisymmetric Bodies at High Reynolds Numbers. Experimental investigation of hydrodynamic force coefficients over AUV hull form. Ocean Engineering, Vol. 36, No. 1. Design of axisymmetric bodies with minimum transonic drag. The present measurements confirm the earlier measurement by Güven. The well- known drop in drag coefficient in the critical Reynolds regime (2 × 10 5.


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An investigation of the transonic pressure drag coefficient for axi-symmetric bodies by Eddy Priyono Download PDF EPUB FB2

REPORTDOCUMENTATIONPAGE FormApprovedOMBNo Publicreportingburdentorthiscollectionofinformationisestimatedtoaverage 1hourperresponse.

title and subtitle an investigation of the transonic viscous drag coefficient for axi-symmetric bodies 6. author(s) yue sang fan 7.

performing organization name(s) and address(es) naval postgraduate school monterey ca 9. sponsoring/monitoring agency name(s) and address(es) funding numbers performing organization report number An investigation of the transonic pressure drag coefficient for axi-symmetric bodies.

By Eddy Priyono. Download PDF (6 MB) distribution is unlimitedThis thesis investigates the pressure drag coefficient in the transonic regime over an axi-symmetric body, with a set of unique contour surfaces developed in a previous thesis.

but also to Author: Eddy Priyono. Viscous drag in the transonic regime over an axi-symmetric body with a unique aft contour surface is investigated. The forebody is composed of an arbitrary ellipsoid. The unique aft contour surface has been obtained by an exact solution of the small perturbation transonic equation, using guidelines and tools developed at the Naval Postgraduate Author: Yue Sang Fan.

An Effective method of calculating transonic flows and wave drag of axisymmetric and 3-D elongate bodies within framework of transonic equivalence rule.

A.S. Fonarev1, J.T. Madhani1 and M.A. Naida2 1School of Aerospace, Mechanical and Mechatronic Engineering University of Sydney, NSWAUSTRALIA 2 CIBC,National Support and Consulting.

The drag coefficient for an airfoil as a function of Mach number at subsonic speeds is sketched qualitatively in Fig. Over a large part of the Mach number range, c d is relatively constant. This pertains to the completely subsonic flow over the airfoil, as sketched in Fig.

the freestream Mach number is increased, the flow Mach number on the top surface of the airfoil also increases. Shaping of axisymmetric bodies for minimum drag in incompressible flow. Comparison of design methods for negative pressure gradient rotary bodies: A CFD study.

30 January | PLOS ONE, Vol. 15, No. Design of axisymmetric bodies with minimum transonic drag. Transonic and supersonic flows past a pair of bodies have been experimentally investigated. The leading bodies were spheres, cylinders, and cones, while the trailing bodies were flat-ended circular cylinders.

The leading and trailing bodies were joined by cylindrical rods of various lengths, aligned with the axis of symmetry. AlAA Pressure Drag Calculations on Axisymmetric Bodies of Arbitrary Moldline B. Drew and A. Jenn McDonnell Douglas Missile Systems St. Louis, MO 28th Aerospace Sciences Meeting January/Reno, Nevada For permission to copy or republish, contact the American institute of Aeronautics and Astronautics.

pressure drag is more significant in blunt objects [5]. Fig. (1) shows the net drag force acting on a cylinder. The drag force is often non-dimensionalized as a function of Reynolds number.

This is then referred to as the drag coefficient (eq. Similarly, the pressure acting on each. The experiments were conducted in an 8-foot transonic pressure tunnel at Mach numbers from to and over a lift coefficient range up to [Show full abstract] A semispan model was.

All three types of cavities reduced the body drag for small cavity depths, with a maximum drag coefficient reduction of being obtained with a ventilated cavity diameters deep. The reductions are an order of magnitude lower than those reported for two-dimensional bodies, but are achieved with a much shorter cavity depth.

The aerodynamic characteristics of models of pairs of bodies on the flow acceleration and deceleration intervals are investigated experimentally at transonic and supersonic flow velocities. The dependence of the drag coefficient of the pair model on the relative drag of the leading body is determined for supersonic velocities.

These laws connect non-dimensional parameters such as pressure coefficient, lift and drag coefficients on families of affinely related bodies of different thickness or slenderness ratio and angle.

Drag coefficient trends for streamlined bodies of revolution. Photograph of oil flow visualization. Free transition. RL = x lo6 Photograph of liquid crystal flow visualization. Free transition.

RL = x lo6. Comparison of drag characteristics with uncorrected Hansen & Hoyt data. title and subtitle an investigation of the 5. funding numbers transonic pressure drag coefficient for axi-symmetric bodies 6.

author(s) eddy priyono 7. performing organization name(s) and address(es) 8. performing naval postgraduate school organization monterey ca report number 9.

Figures 16 and 17 show that the total drag coefficient and the pressure drag coefficient basically increase as the Mach number increases. They rapidly change under the subsonic and transonic condition with increasing the Mach number.

Abstract. The numerous experiments that have been made on drag-reducing devices for two-dimensional bluff bodies have been used as a guide to indicate promising lines of investigation for axi-symmetric bodies.

For the latter case, experiments on splitter plates, cylindrical extensions, base bleed and ventilated cavities are reviewed. Any object moving through a fluid experiences drag - the net force in the direction of flow due to pressure and shear stress forces on the surface of the object.

The drag force can be expressed as: F d = c d 1/2 ρ v 2 A (1) where. F d = drag force (N) c d = drag coefficient. ρ = density of fluid ( kg/m 3 for air at NTP) v = flow velocity (m/s).

An experimental investigation of spontaneous and forced transition on a secant-ogive-nose axisymmetric body was conducted for length Reynolds numbers. In experiments at transonic motion speeds usually it is necessary to apply bodies of simple geometric shape having a property of self-stabilization of the motion [1, 2].

It should note the technical complexity of obtaining the sufficiently detailed picture of the flow around bodies in such experiments. It is stipulated not only by high motion.Distributions of static pressure coefficient over the afterbody and axisymmetric nozzles of a generic, twin-tail twin-engine fighter were obtained in the Langley Foot Transonic Tunnel.The Effect of Nose Blunting on the Wave Drag of Ogive Forebodies - Volume 33 Issue 3 - R.

Partington, T.J. Baker.