Accession Number : AD0701153

Title :   CALCULATION OF PLANE STEADY TRANSONIC FLOWS,

Corporate Author : BOEING SCIENTIFIC RESEARCH LABS SEATTLE WASH

Personal Author(s) : Murman,Earll M. ; Cole,Julian D.

Report Date : JAN 1970

Pagination or Media Count : 40

Abstract : Steady transonic flow past thin airfoils is formulated using small disturbance theory. The governing transonic potential equation is a non-linear mixed (Elliptic-hyperbolic) differential equation. A boundary value problem is formulated and an analytical far field solution derived. For the near field a mixed finite difference system is developed to solve the transonic equation including cases with imbedded shock waves. Results are presented for non-lifting circular arc airfoils and a Nieuwland airfoil. Agreement with experiment for the circular arc airfoils, and exact theory for the shock free Nieuwland airfoil is excellent. (Author)

Descriptors :   (*AIRFOILS, *TRANSONIC FLOW), BOUNDARY VALUE PROBLEMS, DIFFERENTIAL EQUATIONS, SHOCK WAVES, TRANSONIC CHARACTERISTICS, NUMERICAL ANALYSIS

Subject Categories : Aerodynamics
      Aircraft
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE