Abstract:
The interest in STOL airliners was reflected in the
choice of a 100-118 passenger short range aircraft of this
type as the 1971 design project. In addition to the use of
the study for detailed investigation by the students of
Aircraft Design it also served as the basis for an
investigation of the low speed lift and control problems
of STOL aircraft.
This report is concerned with a description of the
configuration adopted and specification of geometric and
aerodynamic data. As such it is the first part of the
complete reporting of the investigation, subsequent parts
being concerned with the more detailed work.
The aircraft was designed to operate from 2000 ft long
single runways and have a cruising speed of up to 11 - 0.83
at 30,000 ft altitude. The estimated gross weight is
115,000 lb and when landing at 100,000 lb weight the approach
speed is 79 knots. The high lift coefficients necessitated
by this are obtained either by externally blown jet flaps or
an augmenter wing arrangement.
