Aeroelasticity
Aeroservoelasticity
Flutter
Flight Loads
ZONAIR Engineering Modules and Capabilities
At each panel, both Dirichlet boundary condition and Neumann boundary condition are imposed for solving the source and doublet strengths (Figure FE.3). Also, the zeroforce condition is imposed on the wake to satisfy the wake condition.
Figure AD.1 Comparison of ZONAIR and PANAIR Paneling Schemes.
(a) Cp on Regular Panels
(b) Cp on Random Panels
Figure AD.2 Regular and Random Paneling of a Sphere at M=0.0, AoA=0 deg..
Force and Moment Coefficients of a Generic Advanced Fighter M = 1.2 and 2.0 ZONAIR vs. Wind Tunnel Test Results
Pressure Distribution on Generic Advanced Fighter at M = 1.2, α = 4.1 º
Hypersonic Body Employing BentNose Control ZONAIR comparison vs. CFL3D
Computed wake shape for a LMSC Rattayya’s blunt body at α = 0 º and M = 0.0 (view of the meridian plane)


Comparison of surface pressure distributions for a conecylinder body (L/d = 3.3) at α = 0 º and M = 0.0 and Cpb = 2.4
Compact Kinetic Energy Missile (CKEM) Flying 5Inches Above the Ground at Mach 2.0 ZONAIR vs. CFL3D Results
Static Aeroelastic Deformation 
Stress Distribution 
Comparison of Cp between the CFD results and the interpolated ZONAIR results on the X34 at M = 10, α =5°.