A Computer Program for the Aerodynamic Design of Axisymmetric and Planar Nozzles for Supersonic and Hypersonic Wind Tunnels
Abstract
A computer program is presented for the aerodynamic design of axisymmetric and planar nozzles for supersonic and hypersonic wind tunnels. The program is the culmination of the effort expended at various times over a number of years to develop a method of designing a wind tunnel with an inviscid contour which has continuous curvature and which is corrected for the growth of the boundary layer in a manner such that uniform parallel flow can be expected at the nozzle exit. The continuous curvature is achieved through specification of a centerline distribution of velocity (or Mach number) which has first and second derivatives that (1) are compatible with a transonic solution near the throat and with radial flow near the inflection point and (2) approach zero at the design Mach number. The boundary-layer growth is calculated by solving a momentum integral equation by numerical integration.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1978
- Accession Number
- ADA062944
Entities
People
- J. C. Sivells
Organizations
- Arnold Engineering Development Complex