A semiempirical expression for boundary-layer transition location is developed based on the concept of a critical ratio of inertial to viscous shearing stresses at laminar breakdown. Extensive comparisons between predicted and measured transition locations on a 10-deg included-angle cone at transonic speeds are shown with the data predicted to within 10%. Comparisons are also made with low subsonic and supersonic data which indicate the method is extendible to these flow regimes. (Author).

A three-dimensional chimera grid-embedding technique is described. The technique simplifies the construction of computational grids about complex geometries. The method subdivides the physical domain into regions which can accommodate easily generated grids. Communication among the grids is accomplished by interpolation of the dependent variables at grid boundaries. The procedures for constructing the composite mesh and the associated data structures are described. The method is demonstrated by solution of the Euler equations for transonic flow about three ellipsoid bodies in close proximity, a wing/body, and a wing/body/tail. Keywords: Grid-embedding techniques, Computational fluid dynamics, Computer programs, Chimera-grid solution, Finite-difference techniques, Transonic flow, Domain-decomposition techniques, Grid-adapting methods.

Smoke emissions were measured in general accordance with the methods specified in the Society of Automotive Engineers Aerospace Recommended Practice 1179. Measurements were made from 1 in. to 32 ft aft of the nozzle exit along the engine centerline, and both horizontally and vertically across the exhaust plume. The J85-GE-5 turbojet engine was operated over a power range from idle to maximum afterburning. The effects of inlet temperature and humidity on smoke production were determined, and trends of smoke production versus power setting were established. (Author).