Two Dimensional Compressible Flow Analysis over a Generic Cruise Missile Model

2013 ◽  
Vol 465-466 ◽  
pp. 358-362
Author(s):  
Hasan Taher M. Elkamel ◽  
Bambang Basuno ◽  
Abobaker Mohammed Alakashi
Keyword(s):  
Mach Number ◽  
Flow Pattern ◽  
Compressible Flow ◽  
Flow Problem ◽  
Flow Analysis ◽  
Angle Of Attack ◽  
Cruise Missile ◽  
Two Dimensional ◽  
Dimensional Flow ◽  
Fluent Software

This study presents Two Dimensional Compressible Flow Analysis Over a Generic Cruise Missile Model. The aerodynamics analysis carried out by use of Fluent Software. Here the pertinent Cruise missile geometry data had been chosen is BGM-109 tomahawk missile. Basically the flow problem around this missile model is a three dimensional flow problem. Treating the flow problem in view as two dimensional flow case, since their result will be used as a comparison purposes with the CFD code which currently under development. The aerodynamics analysis of this missile model carried at the free stream Mach number M = 0.7 for three different angle of attacks α = - 50, 0 and α = 50 . Here the flow is treated as an inviscid compressible flow applied to the missile configuration as (1) fuselage alone, (2) a combined configuration as fuselage and tail and (3) as wing body tail configuration. The results obtained by use of fluent software for those three configurations indicate the flow pattern surrounding object in term of flow properties ( pressure, density and Mach number ) change significantly between the missile as fuselage alone and their other combined configurations. As the angle of attack increase the change of flow pattern surrounding the missile become apparently compared to flow pattern at zero angle of attack. In addition to this, a symmetrical solution between the result at angle of attack α = 50 and α = -50 are also found.

The Two-Dimensional Flow Analysis of Continuous Spiral Reamer Bionic Structure on the Basis of ANSYS

2011 ◽  
Vol 236-238 ◽  
pp. 1576-1580
Author(s):  
Bai Qing Zhang ◽  
Hua Zhu ◽  
Mei Ying Liu
Keyword(s):  
Fractal Structure ◽  
Flow Analysis ◽  
Two Dimensional ◽  
Ansys Software ◽  
Dimensional Flow ◽  
Shape Structure ◽  
Two Dimensional Flow ◽  
Bionic Structure ◽  
Clay Materials

In order to improve the stratification of clay materials in the spiral reamer, we use "bionics method" to modify the structure of the spiral reamer, namely, to add corrugated shape structure to the cutter and hub. Through the analysis of ANSYS software, it is found that corrugated fractal structure can both improve the stratification of clay materials, and increase the yield as well.

Lift and drag in two-dimensional steady viscous and compressible flow

2015 ◽  
Vol 784 ◽  
pp. 304-341 ◽  
Author(s):  
L. Q. Liu ◽  
J. Y. Zhu ◽  
J. Z. Wu
Keyword(s):  
Mach Number ◽  
Viscous Flow ◽  
Compressible Flow ◽  
Velocity Component ◽  
Transverse Velocity ◽  
The Body ◽  
Far Field ◽  
Two Dimensional ◽  
Wide Range ◽  
Lift And Drag

This paper studies the lift and drag experienced by a body in a two-dimensional, viscous, compressible and steady flow. By a rigorous linear far-field theory and the Helmholtz decomposition of the velocity field, we prove that the classic lift formula $L=-{\it\rho}_{0}U{\it\Gamma}_{{\it\phi}}$, originally derived by Joukowski in 1906 for inviscid potential flow, and the drag formula $D={\it\rho}_{0}UQ_{{\it\psi}}$, derived for incompressible viscous flow by Filon in 1926, are universally true for the whole field of viscous compressible flow in a wide range of Mach number, from subsonic to supersonic flows. Here, ${\it\Gamma}_{{\it\phi}}$ and $Q_{{\it\psi}}$ denote the circulation of the longitudinal velocity component and the inflow of the transverse velocity component, respectively. We call this result the Joukowski–Filon theorem (J–F theorem for short). Thus, the steady lift and drag are always exactly determined by the values of ${\it\Gamma}_{{\it\phi}}$ and $Q_{{\it\psi}}$, no matter how complicated the near-field viscous flow surrounding the body might be. However, velocity potentials are not directly observable either experimentally or computationally, and hence neither are the J–F formulae. Thus, a testable version of the J–F formulae is also derived, which holds only in the linear far field. Due to their linear dependence on the vorticity, these formulae are also valid for statistically stationary flow, including time-averaged turbulent flow. Thus, a careful RANS (Reynolds-averaged Navier–Stokes) simulation is performed to examine the testable version of the J–F formulae for a typical airfoil flow with Reynolds number $Re=6.5\times 10^{6}$ and free Mach number $M\in [0.1,2.0]$. The results strongly support and enrich the J–F theorem. The computed Mach-number dependence of $L$ and $D$ and its underlying physics, as well as the physical implications of the theorem, are also addressed.

Aerodynamic Performance Comparison of Airfoils by Varying Angle of Attack Using Fluent and Gambit

2014 ◽  
Vol 592-594 ◽  
pp. 1889-1896 ◽  
Author(s):  
G. Srinivas ◽  
B.P. Madhu Gowda
Keyword(s):  
Lift Coefficient ◽  
Flow Analysis ◽  
Angle Of Attack ◽  
Vital Role ◽  
Performance Comparison ◽  
Operating Conditions ◽  
Aircraft Wing ◽  
Flow Convergence ◽  
Fluent Software ◽  
Wind Tunnel Data

Any aircraft wing is the major component which will play vital role in the generation of lift and at different maneuvering moments throughout the flight. So to maintain this good maneuverability the aircraft wing has to undergo deferent deflections called angle of attack such that the high lift and low drag or vice versa can be settled in the flight. Taking this as the motivation the analysis was carried out on the standard wing airfoil comparing with new designed airfoil. Analyze the numerical simulation values like coefficient of lift, coefficient of Drag, Lift, Drag, and Energy parameters with wind tunnel data to predict accuracy for both the airfoils. Through the selected public literature standard airfoil data and designed airfoil data has been chosen, the geometry was created in the GAMBIT and also the meshing by selecting the suitable c-grid and rectangular grid for the better flow analysis in the FLUENT. The mesh file was imported into the FLUENT software there suitable boundary conditions and operating conditions are given for successful flow convergence. Finally analyzing these results are expecting to be best suitable for good aeromechanical features.

scholarly journals Two-Dimensional Flow Analysis in a Darrieus-Type Water Turbine with Arbitrary-Shaped Duct.

1996 ◽  
Vol 62 (598) ◽  
pp. 2144-2150
Author(s):  
Akinori FURUKAWA ◽  
Kazuki TAKENOUCHI ◽  
Preethisri Ananda GAJANAYAKE ◽  
Kusuo OKUMA
Keyword(s):  
Flow Analysis ◽  
Two Dimensional ◽  
Dimensional Flow ◽  
Two Dimensional Flow ◽  
Water Turbine ◽  
Type Water

Nozzle Discharge Coefficients—Compressible Flow

1974 ◽  
Vol 96 (1) ◽  
pp. 21-24 ◽  
Author(s):  
A. T. Olson
Keyword(s):  
Boundary Layer ◽  
Mach Number ◽  
Compressible Flow ◽  
Approximation Method ◽  
Two Dimensional ◽  
Core Flow ◽  
Flow Discharge ◽  
One Dimensional ◽  
Power Test ◽  
Discharge Coefficients

Using Walz’s approximation method for boundary layer calculation, along with a one-dimensional treatment of the compressible inviscid core flow, discharge coefficients for small nozzle to pipe diameter ratios have been calculated. Discharge co-efficients calculated for the ASME long radius nozzle agree with those recommended by the ASME Power Test Code. In addition, experimental confirmation of an indicated Mach number effect has been achieved in a nozzle modified to minimize two-dimensional effects.

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