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

The addition of wedge-like fairings onto the side of missiles and space launch vehicles,

to shield devices such as cameras and reaction jet nozzles, creates additional drag

particularly when in supersonic and hypersonic freestream flow. An experimental and

computational study was performed in order to obtain aerodynamic data on simple

representative configurations in order to test the accuracy of simple theories for the

drag increment due to these types of fairings. A semi-empirical method to estimate

drag on wedge-shaped projections is presented, which may be used by missile designers

to provide predictions of the drag increment due to wedge-like fairings. The method

is shown to be valid where the wedge width is much smaller than body diameter, and

across the Mach number range 4 – 8.2, but is likely to be valid for higher Mach numbers.

Drag coefficient is found to increase with increasing wedge angle and reducing

wedge slenderness, although increasing slenderness tends to increase skin friction drag.