ANALYSIS OF TRANSONIC FLOW BY MEANS OF PARAMETRIC DIFFERENTIATION.
Final scientific rept., 1 Nov 64-30 Oct 65,
FLUID DYNAMICS RESEARCH LAB MASS INST OF TECH CAMBRIDGE
Pagination or Media Count:
A general method of solving nonlinear partial differential equations was developed and applied to the problem of inviscid transonic flow about airfoils. Soultions are given for nonlifting airfoils at all transonic Mach numbers, including those flows with detached shock waves, and extensions to include lifting and unsteady flows are discussed. Results are given for subsonic and supersonic flow, and for flows at Mach number unity which are in general agreement with other theoretical results and with experiment. Inadequacies in the numerical technique prevented the accurate computation of shock movements, but prelimiliminary results indicate a rearward movement of the shock impinging on the airfoil surface with increasing airfoil thickness, and exhibit the commonly observed rapid acceleration behind the shock. The well known local linearization result of Spreiter and Alksne is shown to be an approximation to the present theory for subsonic flow.
- Fluid Mechanics