.: code RefValues

Calculates main flight parameters based on given values of Mach and Reynolds numbers, using International Standard Atmosphere (ISA) model. Estimates parameters of the grid points distribution (geometric progression coefficient and number of nodes) in turbulent boundary layer for given values of X/Lref and Yplus. Evaluates parameters of turbulent boundary layer on a plate: displacement thickness Dstar, thickness D, and friction coefficient Cf turb (X / Lref).
The user interface is implemented using FOX toolkit library.

.: initial data:

Mach Mach number
To stagnation temperature
Tref temperature at infinity
Re number Reynolds number
Lref Reference lenght
Sref Reference wing area
Angle of attack angle of attack

.: computation results:

C lift lift coefficient
U speed
Ux (Uy or Uz) Cartesian velocity components
Mu dynamic viscosity
Nu kinematic viscosity
Rho density
P pressure
0.5*Rho*U*U dynamic head
S*0.5*Rho*U*U wing loading