Print Email Facebook Twitter Aeroplane Design Study STOL Airliner (A71). Part 1. Configuration description and data Title Aeroplane Design Study STOL Airliner (A71). Part 1. Configuration description and data Author Howe, D. Ward, R.E. Institution Cranfield Institute of Technology, College of Aeronautics Date 1972-06-30 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 M = 0.83 at 35,000 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. Starting in 1946 as the College of Aeronautics, the Cranfield Institute of Technology was granted university status in 1969. In 1993 it changed its name to Cranfield University. To reference this document use: http://resolver.tudelft.nl/uuid:2cdd163f-42a2-4431-87aa-5691125acdea Publisher Cranfield Institute of Technology Source Cranfield Report Aero 12 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1972 Cranfield Institute of Technology Files PDF Cranfield_Report_Aero_No. ... 2-1972.pdf 11.3 MB Close viewer /islandora/object/uuid:2cdd163f-42a2-4431-87aa-5691125acdea/datastream/OBJ/view