Determining Transonic Nose Cone Drag

[SpaceShawn]

According to the OpenRocket techdoc:

A comprehensive data set of the pressure drag coefficient for all nose cone
shapes at all fineness ratios at all Mach numbers is not available. However,
Stoney has collected a compendium of nose cone drag data including data
on the effect of the fineness ratio f N on the drag coefficient and an extensive
study of drag coefficients of different nose cone shapes at fineness ratio 3 [45].
The same report suggests that the effects of fineness ratio and Mach number
may be separated.

Can transonic effects be considered negligible? If so, why and how?

[SpaceShawn]

Transonic effects begin to take effect around Mach 0.8, however they are currently ignored in the model out of simplicity for the first release. This assumption must be stated and made clear