Automated CFD Analysis of Two-Dimensional High-Lift Flows

2002 ◽  
Vol 39 (4) ◽  
pp. 662-667 ◽  
Author(s):  
Anutosh Moitra
Keyword(s):  
Cfd Analysis ◽  
Two Dimensional ◽  
High Lift

STOL Fighter Technology Program

1983 ◽  
Author(s):  
David R. Selegan
Keyword(s):  
Air Force ◽  
Landing Gear ◽  
Two Dimensional ◽  
High Lift ◽  
Technology Program ◽  
Thrust Vectoring ◽  
Design Task ◽  
Advanced Technologies ◽  
Propulsion Control ◽  
Near Term

In recent years, the Air Force has provided additional funds to investigate the technologies and problems associated with providing fighters a Short Take Off and Landing (STOL) capability without seriously degrading today’s maneuver, load, and cruise performance. Within the Flight Dynamics Laboratory, this technology thrust has been planned and organized under the title of “Runway Independence.” The thrust is multi-disciplined in that the following technologies are being investigated both singularly and in integrated combinations to quantify their contribution to providing options in solving the STOL design task. These technologies are: aerodynamics, integrated controls, thrust vectoring/reversing exhaust nozzles, landing gear, and cockpit aids and controllers necessary to operate under weather and/or at night. To help focus these technology efforts and to mature existing technology, the STOL Technology Fighter program was formulated. The objective of the program is to flight validate and mature near-term advanced technologies applicable to providing a STOL capability without sacrificing today’s maneuver, cruise or dash performance. Specific technologies to be addressed in this program are: two-dimensional thrust vectoring/reversing exhaust nozzle; integrated flight/propulsion control; advanced high lift systems; rough/soft field landing gear; and cockpit aids and controllers necessary to locate and land a fighter on the usable portion of the runway at night and in weather. The program will either modify an existing fighter like the F-15, F-16 or F-18 or build a hybrid vehicle like the X-29 with these technologies integrated into the vehicle. The contract will be awarded in 1983 with first flight in late 1987. The end objective of the program is to demonstrate take offs and landings under wet runway conditions of under 1500 feet including dispersion. This paper discusses the integration of these technologies into a total flight program.

Evaluation of RANS Transition Modeling for High Lift LPT Flows at Low Reynolds Number

2013 ◽  
Author(s):  
Kevin Keadle ◽  
Mark McQuilling
Keyword(s):  
Reynolds Number ◽  
Total Pressure ◽  
Current Model ◽  
Pressure Coefficient ◽  
Low Pressure ◽  
Two Dimensional ◽  
High Lift ◽  
Low Pressure Turbine ◽  
Low Reynolds ◽  
Turbine Airfoils

High lift low pressure turbine airfoils have complex flow features that can require advanced modeling capabilities for accurate flow predictions. These features include separated flows and the transition from laminar to turbulent boundary layers. Recent applications of computational fluid dynamics based on the Reynolds-averaged Navier-Stokes formulation have included modeling for attached and separated flow transition mechanisms in the form of empirical correlations and two- or three-equation eddy viscosity models. This study uses the three-equation model of Walters and Cokljat [1] to simulate the flow around the Pack B and L2F low pressure turbine airfoils in a two-dimensional cascade arrangement at a Reynolds number of 25,000. This model includes a third equation for the development of pre-transitional laminar kinetic energy (LKE), and is an updated version of the Walters and Leylek [2] model. The aft-loaded Pack B has a nominal Zweifel loading coefficient of 1.13, and the front-loaded L2F has a nominal loading coefficient of 1.59. Results show the updated LKE model improves predicted accuracy of pressure coefficient and velocity profiles over its previous version as well as two-equation RANS models developed for separated and transitional flows. Transition onset behavior also compares favorably with experiment. However, the current model is not found suitable for wake total pressure loss predictions in two-dimensional simulations at extremely low Reynolds numbers due to the predicted coherency of suction side vortices generated in the separated shear layers which cause a local gain in wake total pressure.

Trend Predictions in Effect of Spoilers for a Mini Car: A Low Cost Solution

2003 ◽  
Author(s):  
N. MathiArasu ◽  
P. S. S. Srinivasan ◽  
K. C. K. Vijayakumar
Keyword(s):  
Finite Element ◽  
Fuel Consumption ◽  
Developing Economies ◽  
Low Cost ◽  
Computation Time ◽  
Computational Time ◽  
Vehicle Stability ◽  
Cfd Analysis ◽  
Two Dimensional ◽  
The World

Most of the CFD analysis on car aerodynamics published so far is being carried out with high-end workstations and many days of computation time, which only few laboratories in the world can afford to. In developing economies like India, many car users use large number of add-on devices, which can have significant impact on the fuel consumption, which they are not aware of. The focus of the present paper is to expose such aspects using a simple personal computer with few hours of computational time, which must be economical. A most popular mini-car on Indian roads is taken for analysis. A two dimensional CFD analysis using commercial finite element based CFD software is used. The analysis has revealed that position and size of front and rear spoilers have significant impact on Lift i.e. vehicle stability and moderate impact on Drag i.e. Fuel consumption. The effect of speed on different geometries is studied and the variations are found to be linear.

Two-dimensional aircraft high lift system design and optimization

1998 ◽  
Author(s):  
Eric Besnard ◽  
Adeline Schmitz ◽  
Edwan Boscher ◽  
Nicolas Garcia ◽  
Tuncer Cebeci
Keyword(s):  
System Design ◽  
Two Dimensional ◽  
High Lift ◽  
Design And Optimization

Noise Reduction in a High Lift Wing Using SMAs: Computational Fluid-Structural Analysis

2016 ◽  
Author(s):  
William Scholten ◽  
Ryan Patterson ◽  
Darren Hartl ◽  
Thomas Strganac ◽  
Jeff Volpi ◽  
...  
Keyword(s):  
Structural Model ◽  
Leading Edge ◽  
Fluid Models ◽  
Cfd Analysis ◽  
High Lift ◽  
Airframe Noise ◽  
Weakly Coupled ◽  
Tunnel Model ◽  
Slat Noise ◽  
Flow Speeds

The leading-edge-slat on an aircraft is a significant contributor to the airframe noise during the low speed maneuvers of approach and landing. It has been shown in previous work that the slat noise may be reduced with a slat-cove filler (SCF). The objective of this current work is to determine how the SMA SCF behaves under steady flow using finite element structural models and finite volume (FV) fluid models based on a scaled wind tunnel model of a newly considered multi-element wing with a SCF. Computational fluid dynamics (CFD) analysis of the wing is conducted at multiple angles of attack, different flow speeds and high lift device deployment states. The FV fluid models make use of overset meshes, which overlap a slave mesh (that can undergo movement and deformation) unto a fixed master mesh, allowing for retraction and deployment of the slat and flap in the CFD analysis. The structural and fluid models are linked using a previously developed framework that permits the use of custom user material subroutines (for superelastic response of the SMA material) in the structural model, allowing for the performance of fluid-structure interaction (FSI) analysis. The fluid and structural solvers are weakly coupled such that the fluid solver transfers pressure data and the structural solver transfers displacements, but the physical quantities of each program are solved independently. FSI results are shown for the cases of the slat/SCF in the fully-deployed configuration as well as for the case of the slat/SCF undergoing retraction in flow.

scholarly journals Two Dimensional Cfd Analysis Of A Hydraulic Gear Pump

2020 ◽  
Author(s):  
Hyun Kim ◽  
Hazel Marie ◽  
Suresh Patil
Keyword(s):  
Gear Pump ◽  
Cfd Analysis ◽  
Two Dimensional

scholarly journals Computational Analysis of High Lift Generating Airfoils for Diffuser Augmented Wind Turbines

2019 ◽  
Author(s):  
Anhad Singh Bajaj ◽  
Jayakrishnan Radhakrishnan ◽  
Raahil Nayak
Keyword(s):  
Fluid Dynamics ◽  
Computational Analysis ◽  
Aerodynamic Performance ◽  
Rotor Blades ◽  
Navier Stokes ◽  
Cfd Analysis ◽  
High Lift ◽  
Actuator Disk ◽  
Computational Fluid Dynamics Cfd ◽  
Flow Through

The present study aims to asses the aerodynamic performance of Diffuser Augmented Wind Turbine (DAWT) using high lift generating airfoils in the construction of the shroud/diffuser. The study is a Computational Fluid Dynamics (CFD) analysis which is carried out using Reynolds Averaged Navier-Stokes (RANS) simulations. The flow across the duct and rotor blades, which are modeled as an actuator disk (AD), is analyzed. Various High-Lift generating airfoils and their geometries were taken into consideration and analyzed with additional geometric modifications, such as a flange, to improve flow through the AD and increase the augmentation factor

Sign in / Sign up

Export Citation Format

Share Document