Hello,
I elected to put some formulae on wikipedia :
https://fr.wikipedia.org/wiki/Altitu...itesse_du_vent
Here are the reverted formulae :
alpha = atan(tas*sin(da)/(tas*cos(da)-GS)
Vw = tas²*sin(da)² + (tas*cos(da)-GS)²
where :
alpha = wind direction - track
da = heading - track
Vw= wind velocity
Careful : formula needs a correction on drift angle, if there is non zero sideslip
What is the aircraft in question ?
It may have more precise info available.