Asymptotic Theory of Transonic Wind Tunnel Wall Interference
Abstract
Two limiting cases are considered related to transonic wall interference. For the first corresponding to slender airplanes, an area rule for interference holds in which the interference of the complete airplane can be obtained from that of its equivalent body of revolution. For large wall height, the slender case exhibits an asymptotic triple deck structure consisting of a cross flow-dominated zone near the model, a weakly perturbed free-field mid field which has a linear multipole far field for solid and free-jet wall conditions. Nonclassical, experimentally determined pressure conditions prescribed on a cylindrical interface lead to a tube vortex far field. For a high aspect ratio second case, the interference is driven by the imaging effect of the interference on the projection of the trailing vortex system in the Trefftz plane. This gives a downwash correction to a near-field nonlinear lifting line flow. Slightly subsonic free stream conditions give a spike like interference flow field due to the shock movement for both limiting cases. Computer codes written to treat these cases, as well as the underlying numerical methods, are described. Approaches integrating the asymptotics with measurement to augment Wall interference Assessment/Correction (WIAC) procedures are outlined.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1991
- Accession Number
- ADA244075
Entities
People
- Chi‐Chin Wu
- H. Jafroudi
- J. D. Cole
- N. D. Malmuth
- R. Mclachlan
Organizations
- Arnold Engineering Development Complex