ScholarLens Back to search
1981•Unpublished venueRequires access

A field panel method for the calculation of inviscid transonic flow about thin oscillating airfoils with shocks

M.H.L. Hounjet

Open publisher page 6 citations

Abstract

A method is described for the calculation of two-dimensional unsteady inviscid transonic flow about thin airfoils, including shock waves. This method, a so-called field panel method, is based on the solution of an integral equation which combines a subsonic lifting surface panel method with subsonic source panels in the flow. These source panels account for nonuniformities in the velocity distribution due to airfoil thickness and incidence. For a NACA 6hA006 and for a NACA 6UA010 airfoil transonic results are presented and compared with results of the LTRAN2-NLR code. The good agreement obtained shows the feasibility of the method. The lower computer cost makes this approach attractive for extension to 3-D flows.

About this research paper

What this paper is about

A method is described for the calculation of two-dimensional unsteady inviscid transonic flow about thin airfoils, including shock waves. This method, a so-called field panel method, is based on the solution of an integral equation which combines a subsonic lifting surface panel method with subsonic source panels in the flow. These source panels account for nonuniformities in the velocity distribution due to airfoil thickness and incidence. For a NACA 6hA006 and for a NACA 6UA010 airfoil transonic results are presented and compared with results of the LTRAN2-NLR code. The good agreement obtained shows the feasibility of the method. The lower computer cost makes this approach attractive for extension to 3-D flows.

Why it matters

OpenAlex reports 6 citations for this work. Citation counts describe recorded attention and do not establish research quality.

Key contribution

A contribution statement is not available in the OpenAlex record.

Method / approach

Method details are not available in the OpenAlex metadata.

Main findings

Findings are not separately available in the OpenAlex metadata.

Limitations

Limitations are not available in the OpenAlex metadata.

Applications

Application details are not available in the OpenAlex metadata.

Available abstract

A method is described for the calculation of two-dimensional unsteady inviscid transonic flow about thin airfoils, including shock waves. This method, a so-called field panel method, is based on the solution of an integral equation which combines a subsonic lifting surface panel method with subsonic source panels in the flow. These source panels account for nonuniformities in the velocity distribution due to airfoil thickness and incidence. For a NACA 6hA006 and for a NACA 6UA010 airfoil transonic results are presented and compared with results of the LTRAN2-NLR code. The good agreement obtained shows the feasibility of the method. The lower computer cost makes this approach attractive for extension to 3-D flows.

Key concepts: Transonic, Airfoil, Inviscid flow, NACA airfoil, Subsonic and transonic wind tunnel, Mechanics, Shock (circulatory), Potential flow

Related papers

Related paper 1Related paper 2Related paper 3
Back to paper searchBrowse research topicsOriginal source
A field panel method for the calculation of inviscid transonic flow about thin oscillating airfoils with shocks — Research Paper | ScholarLens