scholarly journals Aerodynamic Performance of the Inboard Elevon on a Blendedwing- Body Aircraf

2021 ◽  
Author(s):  
Alexander Gordon Jackson
Keyword(s):  
Computational Model ◽  
Numerical Solutions ◽  
Aerodynamic Performance ◽  
Aerodynamic Design ◽  
Trailing Edge ◽  
Negative Deflection ◽  
Average Change ◽  
Implicit Solver ◽  
Blended Wing Body ◽  
Beveled Trailing Edge

The objectives of this research are to examine the effects of trailing edge modifications of the inboard elevon of a blended-wing-body (BWB) aircraft, the goal being to try and reduce the hinge moment of the inboard elevon through selective aerodynamic design. A computational model was built for 60⁰ and 70⁰ beveled trailing edge modifications, as well as no modification. The inboard elevon was deflected positive 5⁰ and negative 5⁰. The numerical solutions were obtained using an implicit solver and inviscid model. The results of this research showed that, through the use of a beveled trailing edge on the inboard elevon, a maximum of 112% reduction in the hinge moment could be achieved for the negative deflection case and a maximum of 88% reduction in the hinge moment for the positive deflection case. The results showed that there was a significant improvement in the hinge moments, with less that a 2% average change in the overall aerodynamic performance of the BWB for the inviscid models.

scholarly journals Aerodynamic Performance of the Inboard Elevon on a Blendedwing- Body Aircraf

2021 ◽  
Author(s):  
Alexander Gordon Jackson
Keyword(s):  
Computational Model ◽  
Numerical Solutions ◽  
Aerodynamic Performance ◽  
Aerodynamic Design ◽  
Trailing Edge ◽  
Negative Deflection ◽  
Average Change ◽  
Implicit Solver ◽  
Blended Wing Body ◽  
Beveled Trailing Edge

The objectives of this research are to examine the effects of trailing edge modifications of the inboard elevon of a blended-wing-body (BWB) aircraft, the goal being to try and reduce the hinge moment of the inboard elevon through selective aerodynamic design. A computational model was built for 60⁰ and 70⁰ beveled trailing edge modifications, as well as no modification. The inboard elevon was deflected positive 5⁰ and negative 5⁰. The numerical solutions were obtained using an implicit solver and inviscid model. The results of this research showed that, through the use of a beveled trailing edge on the inboard elevon, a maximum of 112% reduction in the hinge moment could be achieved for the negative deflection case and a maximum of 88% reduction in the hinge moment for the positive deflection case. The results showed that there was a significant improvement in the hinge moments, with less that a 2% average change in the overall aerodynamic performance of the BWB for the inviscid models.

Geometry and Aerodynamic Performance of Parabolic Trailing-Edge Flaps

2018 ◽  
Author(s):  
Douglas F. Hunsaker ◽  
Jackson T. Reid ◽  
Bruno Moorthamers ◽  
James J. Joo
Keyword(s):  
Aerodynamic Performance ◽  
Trailing Edge ◽  
Trailing Edge Flaps

scholarly journals Features of owl wings that promote silent flight

2017 ◽  
Vol 7 (1) ◽  
pp. 20160078 ◽  
Author(s):  
Hermann Wagner ◽  
Matthias Weger ◽  
Michael Klaas ◽  
Wolfgang Schröder
Keyword(s):  
Noise Reduction ◽  
Leading Edge ◽  
Aerodynamic Performance ◽  
Wing Loading ◽  
Trailing Edge ◽  
Future Directions ◽  
Trailing Edge Noise ◽  
Aerodynamic Properties ◽  
Morphological Adaptations ◽  
Noise Production

Owls are an order of birds of prey that are known for the development of a silent flight. We review here the morphological adaptations of owls leading to silent flight and discuss also aerodynamic properties of owl wings. We start with early observations (until 2005), and then turn to recent advances. The large wings of these birds, resulting in low wing loading and a low aspect ratio, contribute to noise reduction by allowing slow flight. The serrations on the leading edge of the wing and the velvet-like surface have an effect on noise reduction and also lead to an improvement of aerodynamic performance. The fringes at the inner feather vanes reduce noise by gliding into the grooves at the lower wing surface that are formed by barb shafts. The fringed trailing edge of the wing has been shown to reduce trailing edge noise. These adaptations to silent flight have been an inspiration for biologists and engineers for the development of devices with reduced noise production. Today several biomimetic applications such as a serrated pantograph or a fringed ventilator are available. Finally, we discuss unresolved questions and possible future directions.

scholarly journals The numerical solution of the asymptotic equations of trailing edge flow

1974 ◽  
Vol 340 (1620) ◽  
pp. 91-111 ◽  
Keyword(s):  
Boundary Layer ◽  
Outer Layer ◽  
Numerical Solutions ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Trailing Edge ◽  
Navier Stokes Equations ◽  
Boundary Layer Equations ◽  
Asymptotic Equations ◽  
Displacement Thickness

According to Stewartson (1969, 1974) and to Messiter (1970), the flow near the trailing edge of a flat plate has a limit structure for Reynolds number Re →∞ consisting of three layers over a distance O (Re -3/8 ) from the trailing edge: the inner layer of thickness O ( Re -5/8 ) in which the usual boundary layer equations apply; an intermediate layer of thickness O ( Re -1/2 ) in which simplified inviscid equations hold, and the outer layer of thickness O ( Re -3/8 ) in which the full inviscid equations hold. These asymptotic equations have been solved numerically by means of a Cauchy-integral algorithm for the outer layer and a modified Crank-Nicholson boundary layer program for the displacement-thickness interaction between the layers. Results of the computation compare well with experimental data of Janour and with numerical solutions of the Navier-Stokes equations by Dennis & Chang (1969) and Dennis & Dunwoody (1966).

The Effect of Belly-Flap on Aerodynamic Performance of Blended Wing Body Civil Aircraft

2013 ◽  
Vol 378 ◽  
pp. 69-73
Author(s):  
Chen Fang Cai ◽  
Yong Ming Qin ◽  
Jiang Hao Wu
Keyword(s):  
Fluid Dynamics ◽  
Computational Fluid Dynamics ◽  
Angle Of Attack ◽  
Aerodynamic Performance ◽  
Design Parameters ◽  
Flight Safety ◽  
Optimized Design ◽  
Flight Condition ◽  
Civil Aircraft ◽  
Blended Wing Body

The effect of Belly-flap on aerodynamic performance of BWB civil aircraft are investigated in take-off and landing by computational fluid dynamics. And the overload of BWB with Belly-flap also is calculated in the same flight condition. Six parameters are discussed as design parameters of the Belly flap. It is shown that the proper combination of design parameters of Belly-flap can increase the maximum of lift and reduce the angle of attack and nose down moment to improve the flight safety in take-off and landing. When the aircraft with Belly-flap encounters the gust, the maximum overload is very close to 2.5 which are requested by FAR. It is suggested the optimized design of Belly-flap should be done if the Belly-flap is applied in BWB civil aircraft.

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