Thin Layer Navier-Stokes Solutions for Transonic Multibody Interference
Interim rept. Aug 1990-Jan 1991
WRIGHT LAB EGLIN AFB FL ARMAMENT DIRECTORATE
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A thin layer, Navier Stokes flow solver was used to predict the aerodynamics about interfering bodies. Surface pressure distributions compared very well with available experimental data for freestream Mach numbers between 0.60 and 1.20 at an interbody separation distance of 0.8 diameters. Five separate interference regions were identified which contribute to the total interference force, which was an attractive force for all cases investigated. In general, the level of interference increases with increasing free stream Mach number, and decreases with increasing separation distance.
- Fluid Mechanics