Wing-Body and Vertical Tail Interference Effects on Downwash Rate of the Horizontal Tail in Subsonic Flow

Paziresh, Ali; Nikseresht, Amir H.; Moradi, Hashem

doi:10.1061/(asce)as.1943-5525.0000704

Cited by 8 publications

(7 citation statements)

References 15 publications

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“…19 The stagnation temperature T 0 was measured using a resistance temperature detector probe with accuracy of �0.5 K. The base pressure P b was measured by a Druck PDCR42 piezoresistive differential pressure transducer. 9 The data acquisition system consisted of a Teledyne 64 channel "front end" controlled by a PC. The front-end channels for flow parameters transducers were set with 10 Hz, fourth-order lowpass Butterworth filters and appropriate amplification.…”

Section: Wind Tunnel Testingmentioning

confidence: 99%

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Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

Kostić

Bengin

Rašuo

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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The goal of this work is to build a unique numerical method to obtain the basic aerodynamic characteristics of the aircraft and to enable a wide application of the method in the analysis of some aerodynamic characteristics of the aircraft, without use of empirical methods. The Computational fluid dynamics (CFD) simulation method was being calibrated based on test results of the standard AGARD-B (Advisory Group for Aerospace Research and Development) test model, which were obtained in the T-38 trisonic wind tunnel facility of the Military Technical Institute (VTI) in Belgrade, Serbia.The paper presents the CFD simulation through a description of the conditions of flow, geometry of the computer domain, grid density and mesh strategy, boundary conditions, initial strategy and turbulence model. The CFD simulation was carried out for flow cases with similarity parameters M = 0.6, M = 0.85 and M = 1.6 and Re = from 7.7(x106) to 9.9(x106) . The results of calculations were compared with the appropriate experimental ones and presented in the form of comparative diagrams for the drag, lift and pitching moment coefficients. The results of investigation presented in divergence diagrams show very good agreement between numerical and experimental ones. Simulated flows are illustrated by the distribution of pressure and velocity components on the surface of the tested model and the computational domain. This CFD simulation will be applied to other similar aerodynamic designs for a wide range angles of attack and Mach numbers and can be a strong point for the development of different aerodynamic designs.The ultimate aim of the work is to use the previous calibrated CFD simulation method as the basis for future determination of the aerodynamic characteristics of aircraft in non-stationary flight modes, caused by motion of the aircraft and/or by changing the free-velocity vector.

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Section: Wind Tunnel Testingmentioning

confidence: 99%

“…Ali Paziresh et al 9 made a step forward to mesh design by constructing a fully structured grid, used for the whole domain. Aerodynamic coefficients of the horizontal tail of the airplane and also the downwash and downwash rate with respect to the angle of attack of the horizontal tail were investigated.…”

Section: Introductionmentioning

confidence: 99%

Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

Kostić

Bengin

Rašuo

et al. 2020

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

show abstract

“…In calculating aerodynamic forces, viewing the horizontal tail like a miniature main wing will eventually lead to large errors. The horizontal tail should be placed in the main wing wake and be influenced by the downwash effect of the wing [1,2]. That is, the incidence velocity to the horizontal tail is not the velocity at infinity as for the main wing.…”

Section: Introductionmentioning

confidence: 99%

“…If comparing the aerodynamic coefficients on the horizontal tail using 3D simulation method and with those calculated by semi-analytical method based on 2D results, it is necessary to use the formula (2). Because in the semi-analytical method, the horizontal tail is considered a wing alone subjected to a uniform velocity field V  and a downwash angle  determined by semi-analytical method (according to the 3D simulation method, the downwash angle  changes the change in all three directions (x, y, z)).…”

mentioning

confidence: 99%

Investigation of aerodynamics and longitudinal stability of unmanned aerial vehicle with elevator deflection

Ngoc

Binh

2019

Vietnam J. Mech.

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The elevators are usually hinged to the horizontal tail, which acts as a balance and controls the altitude, establishes a steady motion for the aircraft at all lift coefficients. During elevator rotating, the aircraft needs to be stable to establish a new altitude. Longitudinal flying qualities depend on the aerodynamic force of components (wing, tail, fuselage) and configuration of the aircraft. The horizontal tail has a major role in the value of the airplane's pitching moment (due to the long arm from the aerodynamic center of the tail to the center of gravity) for equilibrium and stability of the aircraft. The horizontal tail should be considered an aerodynamic component behind the main wing, influenced by the wing downwash wing rather than just a minor wing. Therefore, method of solving the differential equations for viscous flows through unmanned aerial vehicles (UAV) was used. Small disturbance theory was used to calculate the longitudinal stability of the UAV when controlling the elevator. Flying qualities were assessed so that changes in the aerodynamic characteristics of the wing, tail, fuselage and configuration of the aircraft may be required.

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“…actual thrust in operation is obtained by using the recorded variables in the QAR, in particular the fuel flow rates. Once the thrust models are generated as a function with the flight conditions of climbing, cruise, and descending phases; one can estimate the thrust magnitude by inserting those flight data into the aerodynamic database.When studying the nonlinear and unsteady aerodynamic characteristics of motion, it can be found that the nonlinear and unsteady aerodynamics with hysteresis(Chang et al 2010;Lan and Chang 2018;Paziresh et al 2017) are affected by many parameters of motion state. The aerodynamic models developed by the fuzzy-logic modeling method is very suitable for aerodynamic research of coupling motion, and can be used to enchance the operational efficiency of transport aircraft.…”

mentioning

confidence: 99%

Quantitative Assessment of Dynamic Stability Characteristics for Jet Transport in Sudden Plunging Motion

Wang

Chang

Jiang

2021

Preprint

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The main objective of this article is to present a training program of loss control prevention for the airlines to enhance aviation safety and operational efficiency. The assessments of dynamic stability characteristics based on the approaches of oscillatory motion and eigenvalue motion modes for jet transport aircraft response to sudden plunging motions are demonstrated in this article. A twin-jet transport aircraft encountering severe clear-air turbulence in transonic flight during the descending phase will be examined as the study case. The flight results in sudden plunging motions with abrupt changes in attitude and gravitational acceleration (i.e. the normal load factor). Development of the required thrust and aerodynamic models with the flight data mining and the fuzzy-logic modeling techniques will be presented. The oscillatory derivatives extracted from these aerodynamic models are then used in the study of variations in stability characteristics during the sudden plunging motion. The fuzzy-logic aerodynamic models are utilized to estimate the nonlinear unsteady aerodynamics while performing numerical integration of flight dynamic equations. The eigenvalues of all motion modes are obtained during time integration. The present quantitative assessment method is an innovation to examine possible mitigation concepts of accident prevention and promote the understanding of aerodynamic responses of the jet transport aircraft.

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Wing-Body and Vertical Tail Interference Effects on Downwash Rate of the Horizontal Tail in Subsonic Flow

Cited by 8 publications

References 15 publications

Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

Calibration of the CFD code based on testing of a standard AGARD-B model for determination of aerodynamic characteristics

Investigation of aerodynamics and longitudinal stability of unmanned aerial vehicle with elevator deflection

Quantitative Assessment of Dynamic Stability Characteristics for Jet Transport in Sudden Plunging Motion

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