Thrust Augmented Wing Sections in Potential Flow.
Abstract
A method is presented for calculating the incompressible, potential flow for an arbitrary thrust augmented wing section, possibly experiencing inflow over portions of its surface. The solution includes the shape of an inviscid jet leaving the airfoil calculated by an automatic iteration procedure. The problem is formulated by covering the airfoil-jet surface with line segments which carry velocity discontinuity distributions and satisfy the boundary condition on velocity at the midpoints of the segments. Applying the boundary condition for a particular jet shape leads to a set of linear algebraic equations to be solved for the velocity discontinuity strengths. The final jet geometry is found when the net pressure force for each set of surface elements on the front and back of the jet is balanced by the centrifugal force acting on the fluid within the jet at the corresponding location. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1974
- Accession Number
- AD0786221
Entities
People
- James Dennis Wilson
- John L. Loth
- Subrato Chandra
Organizations
- West Virginia University