Further Studies of Aerodynamic Loads at Spin Entry
Abstract
As part of a continuing investigation of the aerodynamic loads on a fighter-bomber aircraft at spin departure, a coordinated analytical and experimental program was undertaken on vortex shedding from noncircular nose shapes. The asymmetric loads induced by nose vortex shedding at zero and nonzero sideslip are a primary cause for adverse handling qualities at high angles of attack. A theoretical analysis for vortex shedding from noncircular nose shapes at combined angles of attack and sideslip was developed. Boundary layer separation is predicted in order to determine the rate of shedding of vorticity. Comparisons with separation data on two dimensional cylinders and with measured loads and flow field velocities in the wake for inclined ogive-cylinders give reasonable agreement. Tests were conducted in the V/STOL tunnel at NASA Langley Research Center and the Nielsen Engineering + Research water tunnel on a fighter model and typical fighter nose shapes.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 30, 1977
- Accession Number
- ADA047952
Entities
People
- Michael R. Mendenhall
- Selden B. Spangler
Organizations
- Nielsen Engineering & Research (United States)