scholarly journals Influence of Aspect Ratio on Dynamic Stall of a Finite Wing

2018 ◽  
Author(s):  
Ignacio Andreu Angulo ◽  
Phillip J. Ansell
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall ◽  
Finite Wing

Aspect Ratio Effect on Finite Wing Dynamic Stall

2021 ◽  
Author(s):  
Patrick R. Hammer ◽  
Daniel J. Garmann ◽  
Miguel Visbal
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall ◽  
Ratio Effect ◽  
Finite Wing

scholarly journals Influence of Aspect Ratio on Dynamic Stall of a Finite Wing

AIAA Journal ◽  
2019 ◽  
Vol 57 (7) ◽  
pp. 2722-2733 ◽  
Author(s):  
Ignacio Andreu Angulo ◽  
Phillip J. Ansell
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall ◽  
Finite Wing

Experimental Performance of a Trochoidal Propeller with High-Aspect-Ratio Blades

1989 ◽  
Vol 26 (03) ◽  
pp. 192-201 ◽  
Author(s):  
Neil Bose ◽  
Peter S. K. Lai
Keyword(s):  
Aspect Ratio ◽  
High Efficiency ◽  
Open Water ◽  
Finite Amplitude ◽  
Dynamic Stall ◽  
Frictional Drag ◽  
Overall Performance ◽  
Small Ship ◽  
Propeller Performance ◽  
Thrust And Torque

Open-water experiments were done on a model of a cycloidal-type propeller with a trochoidal blade motion. This propeller had three blades with an aspect ratio of 10. These experiments included the measurement of thrust and torque of the propeller over a range of advance ratios. Tests were done for forward and reverse operation, and at zero speed (the bollard pull condition). Results from these tests are presented and compared with: a multiple stream-tube theoretical prediction of the performance of the propeller; and a prediction of the performance of a single blade of the propeller, oscillating in heave and pitch, using unsteady small-amplitude hydrofoil theory with corrections for finite amplitude motion, finite span, and frictional drag. At present, neither of these theories gives a completely accurate prediction of propeller performance over the whole range of advance ratios, but a combination of these approaches, with an allowance for dynamic stall of the blades, should lead to a reliable simple theory for overall performance prediction. Application of a propeller of this type to a small ship is discussed. The aim of the design is to produce a lightly loaded propeller with a high efficiency of propulsion.

Effect of Aspect Ratio on Swept Wing Dynamic Stall

2021 ◽  
Author(s):  
Patrick R. Hammer ◽  
Daniel J. Garmann ◽  
Miguel R. Visbal
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall ◽  
Swept Wing

scholarly journals Dynamic Stall of a Finite-Aspect-Ratio Wing

AIAA Journal ◽  
2019 ◽  
Vol 57 (3) ◽  
pp. 962-977 ◽  
Author(s):  
Miguel R. Visbal ◽  
Daniel J. Garmann
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall

Effect of Sweep on a Pitching Finite Wing

2019 ◽  
Vol 64 (3) ◽  
pp. 1-13 ◽  
Author(s):  
A. D. Gardner ◽  
C. B. Merz ◽  
C. C. Wolf
Keyword(s):  
Boundary Layer ◽  
Single Case ◽  
Suction Side ◽  
Maximum Load ◽  
Boundary Layer Transition ◽  
Dynamic Stall ◽  
Sweep Angle ◽  
Tunnel Wall ◽  
Layer Transition ◽  
Finite Wing

An investigation was performed into the effect of positive and negative sweep angle on the boundary layer transition and dynamic stall behavior of a finite wing. The finite wing had a 6:1 aspect ratio, modern (SPP8) tip shape, and positive twist, moving the maximum load on the wing away from the wind tunnel wall. Experiments were performed with sweep Λ = ±30° and Λ = 0° for static polars and sinusoidal pitching. The positively twisted wing shows a S-shaped boundary layer transition on the pressure side similar to that previously seen for helicopter rotor blades in hover. The transition positions on the suction side of the wing are comparable for the same local angle of attack at all values of the sweep at each of the three pressure sections, and for dynamic pitching motions a hysteresis around the static transition positions is seen. Sweeping the wing led to later stall and higher maximum lift for both static polars and dynamic stall, except for a single case. The negative aerodynamic damping is worse for the swept wing than for the unswept wing, except where the delay of stall led to the flow remaining attached.

scholarly journals Effect of Sweep on Dynamic Stall of a Pitching Finite-Aspect-Ratio Wing

AIAA Journal ◽  
2019 ◽  
Vol 57 (8) ◽  
pp. 3274-3289 ◽  
Author(s):  
Miguel R. Visbal ◽  
Daniel J. Garmann
Keyword(s):  
Aspect Ratio ◽  
Dynamic Stall

Dynamic Stall Simulations on a Pitching Finite Wing

2017 ◽  
Vol 54 (4) ◽  
pp. 1303-1316 ◽  
Author(s):  
Kurt Kaufmann ◽  
Christoph B. Merz ◽  
Anthony D. Gardner
Keyword(s):  
Dynamic Stall ◽  
Finite Wing

scholarly journals Numerical Study on Dynamic-Stall Characteristics of Finite Wing and Rotor

2019 ◽  
Vol 9 (3) ◽  
pp. 600 ◽  
Author(s):  
Qing Wang ◽  
Qijun Zhao
Keyword(s):  
Numerical Study ◽  
Three Dimensional ◽  
Tip Vortex ◽  
Dynamic Stall ◽  
Navier Stokes ◽  
Governing Equations ◽  
Third Order ◽  
Finite Wing ◽  
Wing Tip ◽  
Spanwise Flow

To study the three-dimensional effects on the dynamic-stall characteristics of a rotor blade, the unsteady flowfields of the finite wing and rotor were simulated under dynamic-stall conditions, respectively. Unsteady Reynolds-averaged Navier–Stokes (URANS) equations coupled with a third-order Roe–MUSCL spatial discretization scheme were chosen as the governing equations to predict the three-dimensional flowfields. It is indicated from the simulated results of a finite wing that dynamic stall would be restricted near the wing tip due to the influence of the wing-tip vortex. By comparing the simulated results of the finite wing with the spanwise flow, it is indicated that the spanwise flow would arouse vortex accumulation. Consequently, the dynamic stall is restricted near the wing root and aggravated near the wing tip. By comparing the simulated results of a rotor in forward flight, it is indicated that the dynamic stall of the rotor would be inhibited due to the effects of the spanwise flow and Coriolis force. This work fills the gap regarding the insufficient three-dimensional dynamic stall of a helicopter rotor, and could be used to guide rotor airfoil shape design in the future.

Sign in / Sign up

Export Citation Format

Share Document