Main body design

So the wing is now designed from the NACA 0016 airfoil but there one problem , how do we know that we are getting the require drag and lift ?? , the answer is simple just put your airfoil model into simscale and use C(D) vs C(L) graph from your cfd post process result , okay now we have our data after 10 Mins of simulation , but oh its is newtons… now we will use the equation that every engineers use this formula

Force(Newtons) = C(D) * 1/2 * p * V^2 * A

Notations

• C(D) = coefficient of drag
• p = density of air
• V = velocity
  -A = area

so after some mind soaring calculations you get 24.82 Grams of drag per wing yeppe , congratulations ! you have successfully got a low drag and zero lift wing !!

apart from all of this accurate and precise modeling is done for low error model , just joining the wings to the core testing a locking mechanism making few adjustments in models and making the model aerodynamic

that’s it for this devlog folks nothing more !

sources used :

Simscale - CFD - Incompressible , V : 88.3 m/s