A Fowler Flap System for a High-Performance General Aviation Airfoil

Wentz, W. H.; Seetharam, H. C.

doi:10.4271/740365

Cited by 24 publications

(5 citation statements)

References 2 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The pressure contours in the flow field are illustrated inFigure 27(b). The computed pressure coefficient on the aerofoil surface agrees well with the experimental data (Wentz and Seetharam[47]) as displayed inFigure 27(a).…”

supporting

confidence: 82%

GPU computing of compressible flow problems by a meshless method with space-filling curves

Wang

2014

Journal of Computational Physics

View full text Add to dashboard Cite

A graphic processing unit (GPU) implementation of a meshless method for solving compressible flow problems is presented in this paper. Least-square fit is used to discretise the spatial derivatives of Euler equations and an upwind scheme is applied to estimate the flux terms. The compute unified device architecture (CUDA) C programming model is employed to efficiently and flexibly port the meshless solver from CPU to GPU. Considering the data locality of randomly distributed points, space-filling curves are adopted to re-number the points in order to improve the memory performance. Detailed evaluations are firstly carried out to assess the accuracy and conservation property of the underlying numerical method. Then the GPU accelerated flow solver is used to solve external steady flows over aerodynamic configurations. Representative results are validated through extensive comparisons with the experimental, finite volume or other available reference solutions. Performance analysis reveals that the running time cost of simulations is significantly reduced while impressive (more than an order of magnitude) speedups are achieved.

show abstract

supporting

confidence: 82%

GPU computing of compressible flow problems by a meshless method with space-filling curves

Wang

2014

Journal of Computational Physics

View full text Add to dashboard Cite

show abstract

“…To gain confidence in the application and use of the code in the GACC research program, a test case was run for a GAW(1) airfoil. A comparison of GAW(1) lift coefficient data with two independent experimental studies 22,23 showed favorable results, (figure 11).…”

Section: Cfd Analysismentioning

confidence: 90%

An Active Flow Circulation Controlled Flap Concept for General Aviation Aircraft Applications

Jones

Viken

Washburn

et al. 2002

1st Flow Control Conference

View full text Add to dashboard Cite

“…The configuration used in this report was the LEAPTech high-lift wing with a 40° flap deflection and DEP system that was tested on the HEIST truck. The wing consisted of the NASA GAW-1 airfoil with a fullspan 30% chord Fowler flap [5] and 18 propellers mounted on electric motors in nacelles upstream of the wing leading edge. The tip nacelles on the test article did not include the electric cruise motors that would be present to power the cruise propellers in a real airplane application.…”

Section: Configurationmentioning

confidence: 99%

Computational Analysis of Powered Lift Augmentation for the LEAPTech Distributed Electric Propulsion Wing

Deere

Viken

Carter

et al. 2017

35th AIAA Applied Aerodynamics Conference

View full text Add to dashboard Cite

A computational study of a distributed electric propulsion wing with a 40° flap deflection has been completed using FUN3D. Two lift-augmentation power conditions were compared with the power-off configuration on the high-lift wing (40° flap) at a 73 mph freestream flow and for a range of angles of attack from -5 degrees to 14 degrees. The computational study also included investigating the benefit of corotating versus counter-rotating propeller spin direction to powered-lift performance. The results indicate a large benefit in lift coefficient, over the entire range of angle of attack studied, by using corotating propellers that all spin counter to the wingtip vortex. For the landing condition, 73 mph, the unpowered 40° flap configuration achieved a maximum lift coefficient of 2.3. With high-lift blowing the maximum lift coefficient increased to 5.61. Therefore, the lift augmentation is a factor of 2.4. Taking advantage of the fullspan lift augmentation at similar performance means that a wing powered with the distributed electric propulsion system requires only 42 percent of the wing area of the unpowered wing. This technology will allow wings to be 'cruise optimized', meaning that they will be able to fly closer to maximum lift over drag conditions at the design cruise speed of the aircraft.

show abstract

A Fowler Flap System for a High-Performance General Aviation Airfoil

Cited by 24 publications

References 2 publications

GPU computing of compressible flow problems by a meshless method with space-filling curves

GPU computing of compressible flow problems by a meshless method with space-filling curves

An Active Flow Circulation Controlled Flap Concept for General Aviation Aircraft Applications

Computational Analysis of Powered Lift Augmentation for the LEAPTech Distributed Electric Propulsion Wing

Contact Info

Product

Resources

About