A simple method for drag estimation for wedge-like fairings in hypersonic flow

ABSTRACT The addition of wedge-like fairings onto the side missiles and space launch vehicles, to shield devices such as cameras reaction jet nozzles, creates additional drag, particularly when in supersonic hypersonic freestream flow. An experimental computational study was performed obtain aerodynamic data on simple representative configurations test accuracy theories for drag increment due these types fairings. A semi-empirical method estimate wedge-shaped projections is presented, which may be used by missile designers provide predictions shown valid where wedge width much smaller than body diameter, across Mach number range 4–8.2 but likely higher numbers. Drag coefficient found increase with increasing angle reducing slenderness, although slenderness tends skin friction drag.