عنوان

Computational study of the flowfield through a cascade of NACA 0012 airfoils

Number

TLpq304221435

.Language of Text, Soundtrack etc

انگلیسی

Title Proper

Computational study of the flowfield through a cascade of NACA 0012 airfoils

General Material Designation

[Thesis]

First Statement of Responsibility

M. N. Ahmed

Name of Publisher, Distributor, etc.

King Fahd University of Petroleum and Minerals (Saudi Arabia)

Date of Publication, Distribution, etc.

1995

Specific Material Designation and Extent of Item

118

Dissertation or thesis details and type of degree

M.S.

Body granting the degree

King Fahd University of Petroleum and Minerals (Saudi Arabia)

Text preceding or following the note

1995

Text of Note

Numerical simulation of flow past airfoils is important in the aerodynamic design of aircraft wings and turbomachinery components. These lifting devices often attain optimum performance at the condition of onset of separation. Therefore separation phenomena must be included if the analysis is aimed at practical applications. Consequently, in the present study, numerical simulation of steady flow in a linear cascade of NACA 0012 airfoils is accomplished using a numerical scheme employing control volume approach. The flow field is determined by solving two dimensional incompressible Navier-Stokes equations while the effects of turbulence are accounted for by the k-usd\varepsilonusd model. Separation point at the airfoil surface is predicted at high angles of attack. Pressure, lift and drag coefficients are computed and the results are compared with the predictions of isolated single NACA 0012 airfoil. The study is extended to include the effects of stagger angle of the cascade and rotating boundaries of the isolated airfoil on the flow characteristics. It is found that increase in solidity and/or stagger angle increases the angle of attack at which separation occurs and pressure, lift and drag coefficients are highly influenced by the angle of attack and the solidity ratios. For the case of airfoil leading edge rotation a reduction in the wake size is predicted at high angle of attack. For this case an increase in the lift and a decrease in the drag coefficient is also predicted.

Aerospace materials

Applied sciences

Mechanical engineering

M. N. Ahmed

Electronic name

p

[Thesis]

276903

a

Y