Transonic Interference Flow-Field Analysis for Wing-Body-Pylon-Store Configurations
Abstract
An approximate method to compute the flow-field velocities around wing-body-pylon-store configurations is presented. The method adds transonic non-linear velocities to the linear velocities, computed using Hess's panel method. The non-linear effects are computed by an Integral Equation method derived for three-dimensional transonic small disturbance equations. A viscous/ inviscid interaction procedure incorporates Cebeci's two-dimensional small cross flow boundary layer computations. Viscous effects over lifting and non-lifting bodies are included. The viscous effects can be simulated by either the displacement or blowing method. Also outlined is the inclusion of weak separation and wake effects in the interaction procedure. An internal flow correction is applied to predict the flow in the region between the store and the wing. A finite difference scheme to solve the full potential equations over an axisymmetric body is used to compute the transonic non-linear effects for the store-on-body pressure computation. The results obtained by the above methods are compared with the experimental results at various free stream Mach numbers and angles of attack. The results compare well at all regions except where significant interference effects are predominant, as in the case of flowfield points situated underneath the wing at 0 angle of attack and above a thick store.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1983
- Accession Number
- ADA141811
Entities
People
- P. Sundaram
- S. N. Chaudhuri
Organizations
- University of Tennessee Space Institute