Last is Cd
The drag coefficient is based on standardized shapes' drag.
I use flat plate for un-streamlined
hemisphere for partially streamlined
sphere for streamlined.
I consider 'airframe' to only allow aero controls and aero lift, but not a level os streamlining.
Compare a WW1 Voisin bomber to a teardrop shape; the teardrop shape is certainly more streamlined than the antique bomber, but the bomber has aero controls and lift.
For simplicity, the base Cd for
un-streamlined = .9
partial streamline = .4
streamline = .1
the final Cd value is modified by the fineness ratio involving length. More specifically, by divided the base Cd by the square root of fineness. The fineness ratio is chosen by the designer when creating the hull/fuselage as in the previous post. Use the best ratio using length.
Cd = base_Cd / sqrt ( fineness )
From the previous post, the example ship had a fineness ratio of 5:1
Partial streamlined, the example hull has a Cd = ~ .4 / sqrt ( 5 ) = ~ .178
Had it been streamlined, it'd have a Cd = ~ .045
--------------------------------------------
Now we have density, frontal area and Cd.
Thrust is simply G's acceleration * ship mass.
Ship mass is taken either from a prefered design ruleset, or by using a common convention that 1 dton mass 10 tonnes ( dton displacement * 10 )
So that's everything we need to fill in the equations for top speed in an atmosphere using the standard drag equation rearranged to solve for velocity.
v = sqrt ( (2*Fd) / (p*Cd*A) )
--------------------------------------------------
whew...
hope that didn't scare anyone off
its much easier in a spreadsheet even though its simple enough for a calculator, pencil and paper
The drag coefficient is based on standardized shapes' drag.
I use flat plate for un-streamlined
hemisphere for partially streamlined
sphere for streamlined.
I consider 'airframe' to only allow aero controls and aero lift, but not a level os streamlining.
Compare a WW1 Voisin bomber to a teardrop shape; the teardrop shape is certainly more streamlined than the antique bomber, but the bomber has aero controls and lift.
For simplicity, the base Cd for
un-streamlined = .9
partial streamline = .4
streamline = .1
the final Cd value is modified by the fineness ratio involving length. More specifically, by divided the base Cd by the square root of fineness. The fineness ratio is chosen by the designer when creating the hull/fuselage as in the previous post. Use the best ratio using length.
Cd = base_Cd / sqrt ( fineness )
From the previous post, the example ship had a fineness ratio of 5:1
Partial streamlined, the example hull has a Cd = ~ .4 / sqrt ( 5 ) = ~ .178
Had it been streamlined, it'd have a Cd = ~ .045
--------------------------------------------
Now we have density, frontal area and Cd.
Thrust is simply G's acceleration * ship mass.
Ship mass is taken either from a prefered design ruleset, or by using a common convention that 1 dton mass 10 tonnes ( dton displacement * 10 )
So that's everything we need to fill in the equations for top speed in an atmosphere using the standard drag equation rearranged to solve for velocity.
v = sqrt ( (2*Fd) / (p*Cd*A) )
--------------------------------------------------
whew...
hope that didn't scare anyone off
its much easier in a spreadsheet even though its simple enough for a calculator, pencil and paper