Publication Date:
2019-07-13
Description:
Engine airframe integration effects are investigated for supersonic through-flow fan engines installed on a Mach 3.20 supersonic cruise vehicle. Six different supersonic through-flow fan engine installations covering the effects of engine size, nacelle contour, nacelle placement, and approximate bypass plume effects are presented. The different supersonic through-flow fan installations are compared with a conventional turbine bypass engine configuration on the same basic airframe. The supersonic through-flow fan engine integrations are shown to be comparable to the turbine bypass engine configuration on the basis of installed nacelle wave drag. The supersonic through-flow fan engine airframe integrated vehicles have superior aerodynamic performance on the basis of maximum lift-to-drag ratio than the turbine bypass engine installation over the entire operating Mach number range from 1.10 to 3.20. When approximate bypass plume modeling is included, the supersonic through-flow fan engine configuration shows even larger improvements over the turbine bypass engine configuration.
Keywords:
AERODYNAMICS
Type:
NASA-CR-185140
,
E-5068
,
NAS 1.26:185140
,
AIAA PAPER 89-2140
,
Aircraft Design, Systems and Operations Conference; Jul 31, 1989 - Aug 02, 1989; Seattle, Wa; United States
Format:
application/pdf
