Accession Number:

AD0701153

Title:

CALCULATION OF PLANE STEADY TRANSONIC FLOWS,

Descriptive Note:

Corporate Author:

BOEING SCIENTIFIC RESEARCH LABS SEATTLE WASH

Personal Author(s):

Report Date:

1970-01-01

Pagination or Media Count:

40.0

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

Subject Categories:

  • Aerodynamics
  • Aircraft
  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE