Accession Number:

ADA350226

Title:

Supersonic Flow Past Two Oscillating Airfoils.

Descriptive Note:

Master's Thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

Report Date:

1998-06-01

Pagination or Media Count:

85.0

Abstract:

Supersonic flow past two oscillating airfoils is analyzed using an elementary analytical theory valid for low frequencies of oscillation. The airfoils may have arbitrary stagger angle. This approach generalizes Sauer solution for a single airfoil oscillating at small frequencies in an unbounded supersonic flow. It is shown that this generalization can provide an elementary theory for supersonic flow past two slowly oscillating airfoils. This aerodynamic tool will facilitate the evaluation of pressure distributions and consequently the calculation of moment coefficient. Torsional fluller boundaries are computed. The results for the pitch-damping coefficient are the same when compared with previous analysis. For arbitrary frequencies a linearized method of characteristics was outlined. The elementary theory that has been developed in the thesis can be used for flutter evaluation of aircraft carrying external stores. The result of the thesis is the derivation of the pitch-damping coefficient, which is necessary to predict the flutter conditions.

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE