Alpha_lin.default: Default objective list to create an angle-of-attack analysis

In HaoLi111/rAviExp: Aviation Exploratory

Default objective list to create an angle-of-attack analysis

Description

classified list of basic factors containing zero-lift angle, gradient of Cla, lift induced drag factor, zero-lift drag factor.

Usage

data("Alpha_lin.default")

Format

The format is: List of 4 $ Cla : num 0.1 $ alpha0: num -5 $ CdiF : num 0.0398 $ Cd0 : num 0.02 - attr(*, "class")= chr "Alpha_lin"

Details

Cla: Rate of change of Cl with respect to alpha. alpha0: Corresponded angle of attack when minimum absolute value of lift coefficient occurs Cdif: lift-induced drag factor, also as the factor of the quadratic eq of the Cl versus alpha curve. Correction of the Cdif is usually related to the calculation of the Oswald Spanwise Efficiency. Cd0: Minimum drag coefficient (Usually occurs when lift is close to 0).

References

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

Examples

create(Alpha_lin.default)
## maybe str(Alpha_lin.default) ; plot(Alpha_lin.default) ...

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