Lift coefficient prediction at high angle of attack using recurrent neural network

2003 ◽  
Vol 7 (8) ◽  
pp. 595-602 ◽  
Author(s):  
S. Suresh ◽  
S.N. Omkar ◽  
V. Mani ◽  
T.N. Guru Prakash
Keyword(s):  
Neural Network ◽  
Recurrent Neural Network ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack

High Angle of Attack Parameter Estimation of Cascaded Fins Using Neural Network

2013 ◽  
Vol 50 (1) ◽  
pp. 272-291 ◽  
Author(s):  
Manoranjan Sinha ◽  
Rajesh Ayilliath Kuttieri ◽  
Ajoy Kanti Ghosh ◽  
Ajay Misra
Keyword(s):  
Neural Network ◽  
Parameter Estimation ◽  
Angle Of Attack ◽  
High Angle ◽  
High Angle Of Attack

scholarly journals Numerical Simulation on Aerodynamics of Multi-Element Airfoil with Drooped Spoiler in Ground Effect

2019 ◽  
Vol 37 (1) ◽  
pp. 167-176
Author(s):  
Jiang Liu ◽  
Junqiang Bai ◽  
Guozhu Gao ◽  
Min Chang ◽  
Nan Liu
Keyword(s):  
Lift Coefficient ◽  
Angle Of Attack ◽  
Ground Effect ◽  
Lower Surface ◽  
Navier Stokes ◽  
High Angle ◽  
High Angle Of Attack ◽  
Ride Height ◽  
Navier Stokes Equation ◽  
Sst Turbulence Model

By using the finite volume method and k-ω SST turbulence model to solve the Reynolds Average Navier-Stokes equation and using the slipping wall to simulate the relative movement of the ground, the ground effect on the aerodynamic characteristic of multi-element airfoil with drooped spoiler is investigated numerically, and the reason why the lift coefficient decreased in ground effect is analyzed. The results indicate that, with the reduction in ride height, the lift and the drag decrease and the lift-drag ratio increases for the multi-element airfoil; the amplitude of the reduction in the lift coefficient increases with the reduction in ride height and the increase in the angle of attack, the maximum of lift coefficient can be reduced by about 22%; with the effect of ground, the losses of suction at upper surface make the lift decrease, the increases of pressure at lower surface make the lift increase, the variation of the lift coefficient for the main wing caused by the former is more than three times that of the latter. Analyzing the reason why the lift coefficient decreases showed that:on the one hand, ground effect on the lift coefficient for clean airfoil is changed with the range of angle of attack. For the low-to-moderate angle of attack, the lift coefficient increases; for the high angle of attack, the lift coefficient decreases. But multi-element airfoil works in the takeoff and landing stage for the high angle of attack, which causes the reduction of the lift coefficient in ground effect. On the other hand, the increase of the lift coefficient caused by the deflection of spoiler decreases with the reduction in ride height and the maximum reduction can be about 50%, which illustrates that ground effect makes interaction of the front and back section for the multi-element airfoil weak, resulting in further decreasing the coefficient for the multi-element airfoil.

The Aerodynamics Investigation of Vortex Trap on Helicopter Blade

2012 ◽  
Vol 225 ◽  
pp. 43-48
Author(s):  
M.F. Yaakub ◽  
A.A. Wahab ◽  
Mohammad Fahmi Abdul Ghafir ◽  
Siti Nur Mariani Mohd Yunos ◽  
Siti Juita Mastura Mohd Salleh ◽  
...  
Keyword(s):  
Lift Force ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Strong Wind ◽  
High Angle ◽  
Forward Flight ◽  
High Angle Of Attack ◽  
Helicopter Blade ◽  
Stall Angle ◽  
Cfd Analyses

During helicopter forward flight, the retreating blade revolves at high angle of attack compared to advancing blade in order to balance the lift and also to stabilise the helicopter. However, due to the aerodynamics limitations of the retreating blade at forward flight, stall may occur at high angle of attack compared with the advancing blade. This phenomenon is dangerous for pilot when controlling and balancing the helicopter while flying against strong wind. This paper investigates the capabilities of introducing multiple vortex traps on the upper surface of the helicopter airfoil in order to delay the stall angle of retreating helicopter blade. Blade Element Theory (BET) was applied to scrutinize the lift force along the helicopter blade. Computational Fluid Dynamic (CFD) analyses using the Shear-Stress Transport (SST) turbulence model was carried out to investigate the effect of groove on delaying the stall and to predict the separation of flow over the airfoil. Based on the CFD analyses, the optimization of the groove was done by analyzing the numbers and locations of the grooves. Finally, the results from both BET and the CFD analyses were utilised to obtain the lift force achieved by the vortex trap. The study showed that the presence of multiple vortex traps has successfully increased the lift coefficient and most importantly, delaying the stall angle.

scholarly journals Wind Tunnel Testing of Plasma Actuator with Two Mesh Electrodes to Boundary Layer Control at High Angle of Attack

Sensors ◽  
2021 ◽  
Vol 21 (2) ◽  
pp. 363
Author(s):  
Ernest Gnapowski ◽  
Jarosław Pytka ◽  
Jerzy Józwik ◽  
Jan Laskowski ◽  
Joanna Michałowska
Keyword(s):  
Boundary Layer ◽  
Wind Tunnel ◽  
Experimental Research ◽  
Lift Coefficient ◽  
Angle Of Attack ◽  
Experimental Tests ◽  
Plasma Actuator ◽  
High Angle ◽  
Dbd Plasma ◽  
High Angle Of Attack

The manuscript presents experimental research carried out on the wing model with the SD 7003 profile. A plasma actuator with DBD (Dielectric Barrier Discharge) discharges was placed on the wing surface to control boundary layer. The experimental tests were carried out in the AeroLab wind tunnel where the forces acting on the wing during the tests were measured. The conducted experimental research concerns the analysis of the phenomena that take place on the surface of the wing with the DBD plasma actuator turned off and on. The plasma actuator used during the experimental tests has a different structure compared to the classic plasma actuator. The commonly tested plasma actuator uses solid/impermeable electrodes, while in the research, the plasma actuator uses a new type of electrodes, two mesh electrodes separated by an impermeable Kapton dielectric. The experimental research was carried out for the angle of attack α = 15° and several air velocities V = 5–15 m/s with a step of 5 m/s for the Reynolds number Re = 87,500–262,500. The critical angle of attack at which the SD 7003 profile has the maximum lift coefficient is about 11°; during the experimental research, the angle was 15°. Despite the high angle of attack, it was possible to increase the lift coefficient. The use of a plasma actuator with two mesh electrodes allowed to increase the lift by 5%, even at a high angle of attack. During experimental research used high voltage power supply for powering the DBD plasma actuator in the voltage range from 7.5 to 15 kV.

Research on Unsteady Aerodynamics Modeling Based on Back Propagation Algorithm at High Angle of Attack

2013 ◽  
Vol 392 ◽  
pp. 170-177 ◽  
Author(s):  
Hong Biao Wang ◽  
Bin Bin Lv ◽  
Xiao Juan Yang ◽  
Tai Yuan Luo
Keyword(s):  
Neural Network ◽  
Network Model ◽  
Neural Network Model ◽  
Bp Neural Network ◽  
Angle Of Attack ◽  
Unsteady Aerodynamics ◽  
Test Results ◽  
High Angle ◽  
High Angle Of Attack ◽  
Bp Neural Network Model

with the BP algorithm, this paper sets up the High angle of attack unsteady aerodynamic neural network model. By using the large-amplitude pitch oscillation dynamic test data of some slender model in high-speed wind tunnel, this paper trains and verifies the BP neural network model and discusses elements which may influence the arithmetic speed and prediction accuracy of the neural network model. Test results show that the established BP neural network model matches the wind tunnel test results nicely and has relatively good capacity to predict the High angle of attack unsteady aerodynamics.

scholarly journals Leading Edge Blowing to Mimic and Enhance the Serration Effects for Aerofoil

2021 ◽  
Vol 11 (6) ◽  
pp. 2593
Author(s):  
Yasir Al-Okbi ◽  
Tze Pei Chong ◽  
Oksana Stalnov
Keyword(s):  
Boundary Layer ◽  
Angle Of Attack ◽  
Leading Edge ◽  
Boundary Layer Separation ◽  
Shear Instability ◽  
Vortical Flow ◽  
High Angle ◽  
High Angle Of Attack ◽  
Layer Separation ◽  
Aerodynamic Performances

Leading edge serration is now a well-established and effective passive control device for the reduction of turbulence–leading edge interaction noise, and for the suppression of boundary layer separation at high angle of attack. It is envisaged that leading edge blowing could produce the same mechanisms as those produced by a serrated leading edge to enhance the aeroacoustics and aerodynamic performances of aerofoil. Aeroacoustically, injection of mass airflow from the leading edge (against the incoming turbulent flow) can be an effective mechanism to decrease the turbulence intensity, and/or alter the stagnation point. According to classical theory on the aerofoil leading edge noise, there is a potential for the leading edge blowing to reduce the level of turbulence–leading edge interaction noise radiation. Aerodynamically, after the mixing between the injected air and the incoming flow, a shear instability is likely to be triggered owing to the different flow directions. The resulting vortical flow will then propagate along the main flow direction across the aerofoil surface. These vortical flows generated indirectly owing to the leading edge blowing could also be effective to mitigate boundary layer separation at high angle of attack. The objectives of this paper are to validate these hypotheses, and combine the serration and blowing together on the leading edge to harvest further improvement on the aeroacoustics and aerodynamic performances. Results presented in this paper strongly indicate that leading edge blowing, which is an active flow control method, can indeed mimic and even enhance the bio-inspired leading edge serration effectively.

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