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To see if an airfoil can provide enough lift

This project is testing my design of an airplane, aswell as testing the different tail configurations to choose which one I should use.

Simulation of typical aerodynamics forces (drag and lift with their variations) about an F1 in Schools cars from brazilian's teams,  to make assertive changes in geometry. based on a normal track speed (20m/s).

this project is my is for my school purpose

Calculate Drag and lift coefficients of a Cylinder

Lift test on propeller blade to determine which propeller would be the most efficient

Eveluation of Drag and lift Coefficients of UnderTray Design

Evaluate Drag and Lift Coefficients acting on a Cylindrical Body

Determination of Drag and lift of a formula student car

The purpose of this project is to study the influence of different types of winglets placed at the end of a commercial aircraft wing during takeoff. The flow will be considered incompressible and turbulent (kw-sst). The aerodynamic characteristics of the flow (lift, drag, eddies, etc.) will be determined.

In this project we examined the Effect of Boundary Layers on the  NACA 0012 Airfoil. In-compressible fluid flow simulation is selected for the project. Free stream velocity is selected as 10 m/s having A.O.A  10 with the airfoil.

This project aim to retrofit a sailboat rudder to increase the performance of the entire boat, starting from the original rudder and icreasing some parameters (ie the AR..) the final target is ti increase the lift coefficient.

To verify the setup to be used in analysing aerodynamic bodies

Dynamic Angle of Attack on airfoil for testing it for wind turbine

effect of number of propeller blades on the lift and drag/torc of the drone

An experiment to visually demonstrate the difference in lift generation between delta and straight wings, and why the delta wing has a more steady stall.

A study to demonstrate the necessity of winglets in supressing  wingtip vortices which are shed from the ends of wings in airplanes. These velocity fields are visualized for a wing with and without a wingtip attachment. Vortices shed for the latter case is observed.  These  result in performance losses by reducing lift generated which is quantified in the present study. 

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