Unsteady NewtonBusemann flow theory. Part 2: Bodies of revolution
Abstract
Newtonian flow theory for unsteady flow past oscillating bodies of revolution at very high Mach numbers is completed by adding a centrifugal force correction to the impact pressures. Exact formulas for the unsteady pressure and the stability derivatives are obtained in closed form and are applicable to bodies of revolution that have arbitrary shapes, arbitrary thicknesses, and either sharp or blunt noses. The centrifugal force correction arising from the curved trajectories followed by the fluid particles in unsteady flow cannot be neglected even for the case of a circular cone. With this correction, the present theory is in excellent agreement with experimental results for sharp cones and for cones with small nose bluntness; gives poor agreement with the results of experiments in air for bodies with moderate or large nose bluntness. The pitching motions of slender powerlaw bodies of revulution are shown to be always dynamically stable according to NewtonBusemann theory.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 April 1981
 Bibcode:
 1981STIN...8128371H
 Keywords:

 Aerodynamics;
 Bodies Of Revolution;
 Hypersonic Flow;
 NewtonBusemann Law;
 Supersonic Flow;
 Unsteady Flow;
 Blunt Bodies;
 Centrifugal Force;
 Impact Loads;
 Pressure Distribution;
 Reentry Vehicles;
 Stability Derivatives;
 Fluid Mechanics and Heat Transfer