Volterra's Solution of the Wave Equation as Applied to Three-Dimensional Supersonic Airfoil Problems
Abstract
A surface integral is developed which yields solutions of the linearized partial differential equation for supersonic flow. These solutions satisfy boundary conditions arising in wing theory. Particular applications of this general method are made, using acceleration potentials, to flat surfaces and to uniformly loaded lifting surfaces. Rectangular and trapezoidal plan forms are considered along with triangular forms adaptable to swept-forward and swept-back wings. The case of the triangular plan, form in sideslip is also included. Emphasis is placed on the systematic application of the method to the lifting surfaces considered and on the possibility of further application.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jan 01, 1947
- Accession Number
- ADA298733
Entities
People
- Arthur L. Jones
- Harvard Lomax
- Max A. Heaslet
Organizations
- National Aeronautics and Space Administration