Open
Description
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?