An investigation of a tactical cargo aircraft aft body drag reduction based on CFD analysis and wind tunnel tests

Mirzaei, Mehran; Karimi, Mohammad Hadi; Vaziri, Mohammad Ali

doi:10.1016/j.ast.2011.08.001

Cited by 11 publications

(10 citation statements)

References 5 publications

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“…The pressure variations on the Tecnam P2012 are shown in figure 2. The Results obtained were used for the final design of the aircraft Masoud Mirzaei et al [14] computed the drag due to the aft body of a cargo aircraft. A scaled modified model of the passenger jet was subjected to streams of air in a single return wind tunnel at angles of attack between -10 to 20 degrees.…”

Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

Aircraft Fuselage Recent Developments - A Review

Angelo¹,

Potty²,

Rao

et al. 2019

ujme

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Over multiple iterations spanning many years of research a stable and aerodynamically workable fuselage structure has been zeroed down on. The fuselage being the segment holding the passengers and crew requires an immaculate degree of stability during takeoff, landing and flight. Aerodynamic optimisation presupposes every notion of this 'in flight stability'. The recent interest taken in the field of stability under unforeseen air conditions has led to remarkable developments in the field of aerodynamics. This paper attempts to categorically classify these interests into 3 sections-Theoretical, Experimental and Numerical. Various mathematical models and algorithms have been created to study and test the stability of the fuselage under turbulent conditions caused by weather. Turbulence caused by on flight equipment (propellers etc) and methods for its mitigation have also been mentioned. The chine angle analysis of the fuselage reveals that a sharper angle is more favorable in increasing the lift. The study of asymmetrical vortices and its evolution has enhanced the field of aerodynamic optimization. Unconventional aircraft designs like the BWB are studied and compared against the incumbent structures. Various modeling softwares like CATIA have extensively been used to design these structures. A compilation of these recent developments has been presented to those attempting to intensively analyse and study the field of aerodynamic stability.

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Section: Experimental Analysis Of Aircraft Fuselagementioning

confidence: 99%

Aircraft Fuselage Recent Developments - A Review

Angelo¹,

Potty²,

Rao

et al. 2019

ujme

View full text Add to dashboard Cite

show abstract

“…After checking the grid, the implicit solver based on density is selected, because it is more suitable for compressible flow problems and has a faster convergence. Since the airflow around the aircraft body experiences both laminar and turbulent regimes, transition regions and separation points are strongly affected by turbulence modeling in the CFD (computational fluid dynamics) simulations [ 14 ]. So, in this paper, the flow field is turbulent, the turbulence model is more appropriate to solve such problems as near wall flow problems, and is good at solving out the boundary layer problem with an adverse pressure gradient.…”

Section: Numerical Simulation Of Wing Flow Fieldmentioning

confidence: 99%

“…So, in this paper, the flow field is turbulent, the turbulence model is more appropriate to solve such problems as near wall flow problems, and is good at solving out the boundary layer problem with an adverse pressure gradient. As for a turbulence model, the Spalart-Allmaras model is used because it is relatively simple, which is used to figure out an eddy viscosity transport equation [ 14 , 15 ]. As the Spalart-Allmaras model is one kind of Reynolds-average Navier-Stokes (RANS) model [ 16 ], the Reynolds number and the turbulent magnitude are considered accordingly in this paper.…”

Section: Numerical Simulation Of Wing Flow Fieldmentioning

confidence: 99%

Simulation Analysis of Fluid-Structure Interaction of High Velocity Environment Influence on Aircraft Wing Materials under Different Mach Numbers

Zhang

Sun

2018

Sensors

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Aircraft service process is in a state of the composite load of pressure and temperature for a long period of time, which inevitably affects the inherent characteristics of some components in aircraft accordingly. The flow field of aircraft wing materials under different Mach numbers is simulated by Fluent in order to extract pressure and temperature on the wing in this paper. To determine the effect of coupling stress on the wing’s material and structural properties, the fluid-structure interaction (FSI) method is used in ANSYS-Workbench to calculate the stress that is caused by pressure and temperature. Simulation analysis results show that with the increase of Mach number, the pressure and temperature on the wing’s surface both increase exponentially and thermal stress that is caused by temperature will be the main factor in the coupled stress. When compared with three kinds of materials, titanium alloy, aluminum alloy, and Haynes alloy, carbon fiber composite material has better performance in service at high speed, and natural frequency under coupling pre-stressing will get smaller.

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“…For cruise flight velocity of 185 m/s and altitude 6,000 m, and for assumed surface roughness height of h=10 μm, the roughness Reynolds number is Re h =V · h/v=185 · 10 · 10 -6 /0.242 · 10 -4 =76.4. From [10] it follows that Re t =1 · 10 6 gives the transition position of l t =0,170 m. Since the laminar part is very short, it is accepted that the boundary layer of each aircraft part is turbulent. If the surface roughness height was bigger, this assumption would be even more justified, since this means an even shorter laminar boundary layer.…”

Section: The First Part Of the Axial Correctionmentioning

confidence: 99%

“…There are experimental, empirical, and CFD methods used as correction technique data depending on the flow conditions (Reynolds and Mach number effects), geometry, and types of measurements [1], [2], [3], [4], [5]. Many experimental and empirical methods are used in combination with CFD technology for more accurate results [6], [7], [8].…”

Section: Introductionmentioning

confidence: 99%

Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel

Nikolić

Domitrović

Janković

2018

PROMET

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To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.

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An investigation of a tactical cargo aircraft aft body drag reduction based on CFD analysis and wind tunnel tests

Cited by 11 publications

References 5 publications

Aircraft Fuselage Recent Developments - A Review

Aircraft Fuselage Recent Developments - A Review

Simulation Analysis of Fluid-Structure Interaction of High Velocity Environment Influence on Aircraft Wing Materials under Different Mach Numbers

Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel

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