Accession Number : AD0845108

Title :   Air Defense Aerodynamics Design Investigations.

Descriptive Note : Final rept. 1 Jun 67-31 Oct 68,

Corporate Author : AUBURN RESEARCH FOUNDATION AL

Personal Author(s) : Drummond, A. M.

Report Date : 31 OCT 1968

Pagination or Media Count : 39

Abstract : (1) Closed-form solutions to the missile trajectory equations do not yield acceptable results due to the excessive number of restrictions that must necessarily be imposed in order to obtain the desired analytical solution. Practical trajectories cannot be simulated and so comparative studies using closed-form solutions are of doubtful validity. Numerical solution of the equations of motion is indicated, even at the cost of physical insight into the dominant parameter affecting the result; the insight is available from the analytical solution and is also the main motivation for attempting to solve the problem in closed form. However, a comparison between exact and analytical solutions should be made. (2) Estimation procedures for aerodynamic quantities in the Mach Number range from 3 to 6 are not readily available and experiments are indicated to supply the missing data. (3) The results of preliminary calculations show that the winged missile exceeds the performance of the wingless missile, even with a 70 lb. payload penalty and extra weight due to the wings, for the long range interception case against a non-maneuvering target. It is felt that this conclusion will be substantiated when the accurate lift, drag, and pitching moment results are used in the program. (Author)

Descriptors :   (*SURFACE TO AIR MISSILES, AERODYNAMIC CHARACTERISTICS), GUIDED MISSILE TRAJECTORIES, INTERCEPT TRAJECTORIES, DRAG, SUPERSONIC CHARACTERISTICS, EQUATIONS OF MOTION, BOUNDARY VALUE PROBLEMS, BEAM RIDER TRAJECTORIES, GUIDANCE.

Subject Categories : Guided Missile Dynam, Config & Cntrl Surfaces
      Guided Missiles
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE