CALCULATION OF PLANE STEADY TRANSONIC FLOWS,
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1970
- Accession Number
- AD0701153
Entities
People
- Earll M. Murman
- Julian D. Cole
Organizations
- Boeing