Acoustic Noncompactness of a Beveled Trailing Edge Using Incompressible Flow Source Data

AIAA Journal ◽  
2017 ◽  
Vol 55 (5) ◽  
pp. 1757-1762 ◽  
Author(s):  
W. C. P. van der Velden ◽  
A. H. van Zuijlen ◽  
A. T. de Jong ◽  
H. Bijl
Keyword(s):  
Incompressible Flow ◽  
Trailing Edge ◽  
Source Data ◽  
Beveled Trailing Edge

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.

Numerical and experimental investigation of a beveled trailing-edge flow field and noise emission

2016 ◽  
Vol 384 ◽  
pp. 113-129 ◽  
Author(s):  
W.C.P. van der Velden ◽  
S. Pröbsting ◽  
A.H. van Zuijlen ◽  
A.T. de Jong ◽  
Y. Guan ◽  
...  
Keyword(s):  
Experimental Investigation ◽  
Flow Field ◽  
Noise Emission ◽  
Trailing Edge ◽  
Beveled Trailing Edge ◽  
Edge Flow

Prediction of vortex lift of non-planar wings by the leading-edge suction analogy

1988 ◽  
Vol 92 (914) ◽  
pp. 154-164 ◽  
Author(s):  
B. C. Hardy ◽  
S. P. Fiddes
Keyword(s):  
Incompressible Flow ◽  
Three Dimensional ◽  
Leading Edge ◽  
Panel Method ◽  
Good Prediction ◽  
Trailing Edge ◽  
Planar Configuration ◽  
Trailing Edge Flaps ◽  
Lift And Drag ◽  
Acceptable Agreement

SummaryA three-dimensional panel method has been used to calculate edge-suction forces for thin sharp-edged wings in incompressible flow. The suction forces have been used to estimate the vortex lift on the wings by means of the leading-edge suction analogy due to Polhamus.The results for planar wings are in acceptable agreement with other methods based on the suction analogy. A limited comparison with results from experiments for non-planar wings revealed good prediction of lift and drag increments associated with the deflection of leading and trailing edge flaps for ‘conventional’ wings of high sweep, but only moderate agreement for a grossly non-planar configuration.

Tomographic PIV for Beveled Trailing Edge Aeroacoustics

2014 ◽  
Author(s):  
Stefan Pröbsting ◽  
Abhineet Gupta ◽  
Fulvio Scarano ◽  
Yaoyi Guan ◽  
Scott C. Morris
Keyword(s):  
Trailing Edge ◽  
Tomographic Piv ◽  
Beveled Trailing Edge

On the Calculation of the Incompressible Flow Past an Aerofoil with a Jet Flap

1978 ◽  
Vol 29 (1) ◽  
pp. 44-59 ◽  
Author(s):  
R. O’Mahoney ◽  
F.T. Smith
Keyword(s):  
Conformal Mapping ◽  
Incompressible Flow ◽  
Mapping Method ◽  
Jump Conditions ◽  
Trailing Edge ◽  
Planar Flow ◽  
Flow Past ◽  
Free Case ◽  
Circle Mapping

SummaryThe incompressible planar flow past a wing with a jet issuing from the trailing edge is calculated by two separate methods, both adaptations of conformal mapping routines that are numerically exact in the jet-free case. These are the well-known circle mapping method and the halfplane method. The former is rendered inexact by the jump conditions across the jet and an approximation is necessary. The halfplane method, however, remains exact in principle, and a range of results is presented below. The most accurate of the previous calculations is verified, and comparisons between the halfplane and circle methods are also made. The halfplane scheme seems well suited for such wake-controlled flows and has been extended to transonic conditions in a related study.

Unsteady viscous simulation for beveled trailing edge flow fields

1997 ◽  
Author(s):  
Charles Knight ◽  
Leonard Peltier ◽  
Charles Knight ◽  
Leonard Peltier
Keyword(s):  
Flow Fields ◽  
Trailing Edge ◽  
Beveled Trailing Edge ◽  
Edge Flow
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