create.Alpha_lin: Create lift and drag properties with thin airfoil, linear...

In HaoLi111/rAviExp: Aviation Exploratory

Create lift and drag properties with thin airfoil, linear lift theory

Description

Assuming Re is constan, using gradient of Cl with respect to angle of attack(AoA or alpha), zero-lift angle and lift-induced drag factor to generate lift and drag properties. This would only be accurate for a small range of alpha. For more properties see 'Thin Airfoil Theory'.

Usage

create.Alpha_lin(AAR, alpha = seq(from = -5, to = 10, by = 0.1))

Arguments

AAR	classified list of basic factors containing zero-lift angle, gradient of Cla, lift induced drag factor, zero-lift drag factor.
alpha	Domain of angle of attack to loop for.

Author(s)

Hao Li

References

https://en.wikipedia.org/wiki/Airfoil

See Also

Alpha_lin.default

Examples

create(Alpha_lin.default)
##---- Should be DIRECTLY executable !! ----
##-- ==>  Define data, use random,
##--	or do  help(data=index)  for the standard data sets.

## The function is currently defined as
function (AAR, alpha = seq(from = -5, to = 10, by = 0.1))
{
    Cl = AAR$Cla * (alpha - AAR$alpha0)
    Cd = AAR$Cd0 + Cl * Cl * AAR$CdiF
    k = Cl/Cd
    re = list(Raw = AAR, Out = data.frame(alpha = alpha, Cl = Cl,
        Cd = Cd, k = k))
    class(re) = "AlphaOut"
    re
  }

HaoLi111/rAviExp documentation built on Oct. 21, 2022, 2:18 a.m.