Slope Of Lift Coefficient Research Articles

Numerical study on wake galloping of tandem circular cylinders considering the effects of mass and spacing ratios

The mass and spacing ratios of parallel circular cylinder structures change over a wide range in engineering applications. In this study, the effects of mass ratio, spacing ratio and helical wires on the wake galloping of tandem circular cylinders are investigated by LES turbulence model at the subcritical Reynolds number regime. The upstream cylinder is fixed and the downstream one is free to respond in the transverse direction. The characteristics of wake galloping of tandem circular cylinders are systematically studied for the cases of mass ratios m∗ ​= ​1.8, 200 and spacing ratios x0/D ​= ​4, 8 and 12. A critical velocity of wake galloping is derived as a function of mass ratio and lift coefficient slope using a wake-stiffness-based model. The suppression of wake galloping by the 4-start helical wires is examined and the maximum amplitude of vibration is found to decrease by 63% because of the positive added damping generated by helical wires.

Investigation on Propeller Slipstream by Using an Unstructured Rans Solver Based on Overlapping Grids

AbstractBased on unstructured hybrid grid and dynamic overlapping grid technique, numerical simulations of Unsteady Reynolds Averaged Navier-Stokes equations were performed and investigation on isolated propeller aerodynamic characteristics and effects of propeller slipstream on turboprops were undertaken. The computational grid consisted of rotational subzone of propeller and stationary major-zone of aircraft, and walls criterion was used in the automatic hole-cutting procedure. Distance weight interpolation and tri-linear interpolation were developed to transfer information between the rotational and stationary subzones. The boundaries of overlapping grids were optimized for fixed axis rotation. The governing equations were solved by dual-time method and Lower Upper-Symmetric Gauss-Seidel method. The method and grid technique were verified by isolated propeller configuration and the computational results were in well agreement with the experimental data. The grid independence was studied to establish the numerical results. Finally, the flow around a turboprop case was simulated and the influence of propeller slipstream was presented by analyzing the surface pressure contours, profile pressure distribution, vorticity contours and profile streamline. It's indicated that the slipstream accelerates and rotates the free stream flow, changing the local angle of attack, enhancing the downwash effects, affecting the pressure distribution on wing and horizontal tail, as well as increasing the drag coefficient, pitching moment coefficient and the slope of lift coefficient.

A 2D Simulation of the Flow Separation Control over a NACA0015 Airfoil Using a Synthetic Jet Actuator

The present study aims to investigate numerically the flow control possibility using a synthetic jet actuation over a bi-dimensional NACA0015 airfoil manoeuvring at a highly turbulent flow (8.9e105 Reynolds to chord number). The 2-D flow behaviour was computed using the ANSYS Fluent commercial code. The so-called Reynolds Averaged Navier-Stocks (RANS) approach has been tested for one (Spalat-Allmaras S-A) and two (K-ε) transport equations for the turbulence modelling. Both present a weakness to predict the stall angle effectively. The S-A lift coefficient slope seems to be the closest to the experimental data. The synthetic jet control exhibits an extraordinary lift coefficient enhancement at high Angles Of Attack (AOA) but seems to be less obvious at low AOA, where the flow is still attached. A synthetic jet of a Strouhal (St = 2) and momentum (Cμ of 0.56%), delays the stall onset from 15 to 19deg with enhancing the lift coefficient by 40%. The actual work has been enriched by studying the effect of the jet’s frequency and momentum on the lift temporal signal. Also, the interaction between the mean flow and the synthetic jet structures topology was undertaken.

스마트 무인기에 Wingtip Fence 적용

To enhance aerodynamic efficiency of the Smart Un-manned Aerial Vehicle(SUAV) during the transition period, wingtip fence is attached at the end of wing. The application of wingtip fence is to reduce the effect of the separated flow caused by the nacelle on the wing especially when the tilting angle of nacelle is more than 30 degrees. To compare the effect of with and without wingtip fence, flow visualization and measurement of the aerodynamic coefficients using the pyramidal type external balance are done. Result of forces and moments measurement shows that the slope of lift coefficient is increased 18% and rolling moment of SUAV especially 60 & 90-degree tilting is changed in favorable manners with wingtip fence.

Blunt Cones at Angle of Attack in Supersonic Nonuniform Freestreams

A = velocity defect parameter [see Eq. (1)] Ab = local cone cross-sectional area B = wake width parameter [see Eq. (1)] CD = drag coefficient, drag/qnAb CL = lift coefficient, \ift/qnAb CMQ = nose pitching moment coefficient, nose momQnt/qnAbL (positive nose up) CLa = lift coefficient slope, dCJdx CM* = pitching moment coefficient slope, dCMQldoL Cp = pressure coefficient, (p — pn)lqn L = reference length equal to nose radius qn = dynamic pressure based on wake centerline conditions, ' PnVn/2 S' = nondimensional surface distance measured from the apex of a sharp cone, S/L § = nondimensional surface distance measured from the forward stagnation point on a blunt cone, S/L