Zurriati Mohd Ali

Investigation on aerodynamic characteristics of baseline-II E-2 blended wing-body aircraft with canard via computational simulation

Previous wind tunnel test has proven the improved aerodynamic charasteristics of Baseline-II E-2 Blended Wing-Body (BWB) aircraft studied in Universiti Teknologi Mara. The E-2 is a version of Baseline-II BWB with modified outer wing and larger canard, solely-designed to gain favourable longitudinal static stability during flight. This paper highlights some results from current investigation on the said aircraft via computational fluid dynamics simulation as a mean to validate the wind tunnel test results. The simulation is conducted based on standard one–equation turbulence, Spalart-Allmaras model with polyhedral mesh. The ambience of the flight simulation is made based on similar ambience of wind tunnel test. The simulation shows lift, drag and moment results to be near the values found in wind tunnel test but only within angles of attack where the lift change is linear. Beyond the linear region, clear differences between computational simulation and wind tunnel test results are observed. It is recommend...

Static stability of Baseline-II blended wing- body aircraft at low subsonic speed: Investigation via computational fluid dynamics simulation

A study of the effect of canard to Baseline-II blended wing-body aircraft is presented here with emphasis on investigating contributions of canards various setting angle to aerodynamic parameters and longitudinal static stability. A computational fluid dynamic (CFD) simulation has been conducted at low subsonic speed to collect aerodynamic data and found that its aerodynamic trend is similar to many BWB aircraft and consistent to previous studies conducted in UiTM. Canard setting angle affects the value of lift-at-zero incidence of a BWB aircraft, although fairly small for current canard size that it is not adequate to produce positive pitching moment-at-zero lift. Baseline-II is partially, statically stable in longitudinal motion because of negative moment change w.r.t. lift change but it has equilibrium incidence angle that only produces negative lift. Larger canard and/or modification to Baseline-II wing-body are needed to overcome this flaw. The location of new reference point provides ‘comfortable’ static margin. Data and mathematical characteristic obtained from BL-IIA SP CFD simulation is comparable to those from wind tunnel experiment and both show satisfactory-to-good correlation to theoretical calculations.

Effect of canard to the aerodynamic characteristics of Blended Wing Body airplane

This paper describes a series of ongoing wind tunnel experiments of Blended Wing Body equipped with canard as longitudinal control surface. The canard has a rectangular shape with fixed aspect ratio and planform area. All tests were conducted in the subsonic wind tunnel at the Universiti Teknologi MARA, at Mach number of 0.1. Angles of attack, α were varied from -16° to 50°. The lift curve slope, CLα shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The visualization using mini tufts were performed to observe airflow at the upper surface of the canard.

The aerodynamics performance of Blended Wing Body Baseline-II E2

This paper discusses the aerodynamics characteristics of Blended Wing Body — Baseline II E2, unmanned aerial vehicle aircraft. A computational method, Computational Fluid Dynamic (CFD) Star CCM+ software has been performed to obtain the aerodynamics characteristic of the BWB. The aerodynamic characteristics prediction of BWB-Baseline II E2 aircraft was obtained through CFD analysis using unstructured mesh and standard one — equation turbulence model, Spalart-Allmaras was selected in the investigations. Lift coefficient (CL), drag coefficient (CD) and moment coefficient (CM) were studied at flight condition of Mach 0.1 (∼34 m/s) at different angles of attack, α. The CFD results were compared with the experimental result. The results show the trend of lift curves are similar at the linear region (α = −10° to 7°) but at the higher angle of attack the trends become nonlinear. The drag coefficient for CFD simulations is greater than experimental result and there are differences in pitching moment curves between CFD simulation and experiment data which the experiment data shows a steep curve than simulation.

Aerodynamics characteristic of UiTM's BWB UAV Baseline-II at different canard deflection angles at low pitching angle

This paper discusses the influence of canard deflection angle on the aerodynamics characteristic of a Blended Wing Body (BWB) Baseline-II aircraft obtained from wind tunnel test. Canard is added as longitudinal control. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model at around 0.1 Mach number at several canard angle. The result of the lift coefficient (CL), the drag coefficient (CD), and the pitching moment coefficient (CM), are plotted and analyze to show the characteristics of the BWB with different canard deflection angles.

Wind Tunnel experiments of UiTM's blended wing body (BWB) Baseline-II unmanned aerial vehicle (UAV) at low subsonic speed

An experimental investigation is conducted to obtain aerodynamic characteristics and performance of a blended wing-body aircraft (BWB) under study by UiTM. The BWB design for unmanned aerial vehicle (UAV) known as “Baseline-II” is actually a completely-revised, redesigned version of “Baseline-I” BWB. The Baseline-II features have introduced a canard, a simpler planform, and slimmer body compared to its predecessor while maintaining wingspan. All tests are carried out in UiTM Low Speed Wind Tunnel using 1/6 scaled model of BWB at around 0.1 Mach number. The lift coefficient (CL), the drag coefficient (CD), the pitching moment coefficient (CM), and the Lift-to-Drag (L/D) ratio curves are then plotted at various angles of attack, including CL versus CD polar to show the performance of the BWB. The results obtained will show the aerodynamic

The Effect of Canard to the Aerodynamic Behavior of Blended Wing Body Aircraft

This paper presents a study on the effect of canard setting angle on the aerodynamic characteristic of a Blended Wing Body (BWB). Canard effects to BWB aerodynamic characteristics are not widely investigated. Hence the focus of the study is to investigate the variations of lifts, drags and moments when the angles of attack are varied at different canard setting angles. Wind tunnel tests were performed on BWB aircraft with canard setting angles,  ranging from -20˚ to 20˚. Angles of attack,  were varied from -10˚ to 10˚. Aspect ratio and canard planform area were kept fixed. All tests were conducted in the subsonic wind tunnel at Universiti Teknologi MARA, at Mach number of 0.1. The streamlines flow, at the upper surface of the canard was visualized using mini tuft. Result shows that the lift coefficient does not change much with different canard setting angles. As expected, the lift coefficient increases with increasing angles of attack at any canard setting angle. In general, the moment coefficient increases as the canard setting angle is increased. The results obtained in this research will be of importance to the understanding of aerodynamic behavior of BWB employing canard in its configuration.

Longitudinal Flight Dynamics of Baseline-II BWB UAV

The objective of this paper is to investigate longitudinal flight dynamics of the said aircraft at loitering flight condition near sea level. Three mathematical dynamic models are used to compute transient response of Baseline-II E-2 BWB along with a proposed model known as Model-N. Model-N is derived to incorporate as many important derivatives, including gravitational and pitch angle factor, as possible. While all these four dynamic models are different in a sense where one model is more simple or complex than the others, the basic architecture of all these models are the same. This paper shows the short-period mode needs serious attention. A control algorithm is needed to overcome its handicap which is below Level 3 damping ratio according to MIL-F-8785C. Improvement to phugoid can be considered secondary, but one must ensure that bringing short period mode to Level 1 flying quality does not make phugiod mode response worse than it is now.