Accession Number:

ADA070022

Title:

The Transonic Oscillating Flap.

Descriptive Note:

Final rept. Apr-Sep 78,

Corporate Author:

BOEING AEROSPACE CO SEATTLE WASH

Personal Author(s):

Report Date:

1979-05-01

Pagination or Media Count:

21.0

Abstract:

Numerical experiments for the unsteady transonic flow past a symmetric airfoil with an oscillating flap in free air are carried out for a range of supercritical Mach numbers and reduced frequencies using two newly devised computational schemes. The inviscid results, unhampered by the complicating effects of wind tunnel wall interference and shockwave and boundary layer interaction, evaluate the extent to which the unsteady loading responds linearly to changes in flap deflection and also the dependence of shock excursion amplitude and net unsteady lift and moment coefficients on oscillation frequency. The main conclusions are discussed in light of recent experimental findings. Author

Subject Categories:

  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE