Two-Dimensional Unsteady Lift Problems in Supersonic Flight
Abstract
The variation of pressure distribution is calculated for a two-dimensional supersonic airfoil either experiencing a sudden angle-of- attack change or entering a sharp-edged gust. From these pressure distributions the indicial lift functions applicable to unsteady lift problems are determined for the two cases. A close similarity is shown to exist between the calculated functions for varying free-stream Mach number and the corresponding functions in three-dimensional incompressible flow for varying aspect ratio. Results are presented which permit the determination of maximum increment in lift coefficient attained by an unrestrained airfoil during its flight through a gust. As an application of these results, the minimum altitude for safe flight through a specific gust is calculated for a particular supersonic wing of given strength and wing loading.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1948
- Accession Number
- ADA380794
Entities
People
- Harvard Lomax
- Max A. Heaslet
Organizations
- National Aeronautics and Space Administration