1 Introduction

For this tutorial we will be using the same aircraft that was introduced in tutorial 4. It is an 8m span light aircraft. For the estimation of turn rates that will be done later, it should be noted that the distance between the tail and the wings is approximately 4.3m.
 

 

We are going to use a specific analysis in ace of aircraft, that will estimate the change of aerodynamic coefficient for:

• a change of angle of attack. To obtain the dC/dalpha coefficients.
• a change of angle of sideslip. To obtain the dC/dbeta coefficients.
• a change of pitch rate. To obtain the dC/dq coefficients, such as the pitch damping Cmq.
• a change of yaw rate. To obtain the dC/dr coefficients, such as the yaw damping Clr.
• a change of roll rate.To obtain the dC/dp coefficients, such as the roll damping Cnp.

 
This will be done with a NS model first, then with a VLM model, for comparison.
 
For the NS model, please find the igs files in the ACE of Aircraft directory, in the compressed folder named "IGSfiles.zip", or use this link : IGSfiles.zip.