Prediction Methodology for Propulsive Induced Force and Moments of V/STOL Aircraft in Transition/STOL Flight. Volume 1. Technical Discussion.
Abstract
A computerized prediction method for propulsive induced forces and moments in transition and short takeoff and landing (STOL) flight has been developed for the Naval Air Development Center (NADC). The method developed was based on the Vought V/STOL aircraft propulsive effects computer program (VAPE). The VAPE program is capable of evaluating: (1) Effects of relative wind about an aircraft; (2) Effects of propulsive lift jet entrainment, vorticity, and flow blockage; (3) Effects of engine inlet flow in the aircraft flow fields; (4) Engine inlet forces and moments including inlet separation; (5) Ground effects in the STOL region of flight. The effects of relative wind about an aircraft with or without jets and/or inlet effects is determined by a very general three-dimensional potential flow panel method. The effects of the propulsive lift jets are determined by one of three different jet models which have been extensively modified and/or developed at Vought. The effects of engine inlet flow on the aircraft is determined by a NASA Lewis code for axisymmetric inlets which has been modified and automated at Vought. This method will determine the pressures on the inlet face and nacelle inlet lips. The VAPE program will then utilize these pressures to determine the forces and moments acting on the inlet. Calculations may also be done to determine when and where separation occurs on the inlet lip. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 31, 1979
- Accession Number
- ADA103272
Entities
People
- S. S. Kress
- T. D. Beatty
Organizations
- Vought