Angle of attack

Airfoil

Engineering

Wind tunnel

Aerospace engineering

Materials science

Marine engineering

Aerodynamics

Computer science

Jet (fluid)

Geology

Physics

Flow (mathematics)

Wake

Environmental science

Meteorology

Mechanics

Flow Measurement and Instrumentation

An experimental study is conducted to investigate the impact of different parameters on the performance of CFJ0025-065-196 airfoil. For this purpose, an equipped wind tunnel with the motor capacity of 7 kW as well as high-tech measuring instruments are employed, and the impact of attack angle on the average velocity profiles for different jet flow velocities, in addition to the self-similar velocity profiles for different attack angles, and the wake effect are found and discussed comprehensively. The experiments are done for five different values of the attack angle, which are 0, 5, 12, 20, and 25° as well three magnitude for the jet flow velocity, including 0, 19.7, and 32.2 m s−1. According to the results, the attack angle in which the performance of the airfoil decreases has an upward trend when the jet flow velocity increases, and it reaches from 20 to 25° when jet flow velocity changes from 0 to 19.7 m s−1. Moreover, increasing the attack angle from 0 to 12° makes the jet frountier wider whereas a downward trend happens by chaning the attack angle from 12 to 25°. Additionally, the higher the jet velocity is, the weaker wake stream has.

A detailed experimental airfoil performance investigation using an equipped wind tunnel