Flight Envelope Expansion during Prototype Development

Abstract

Certification configuration loads are discussed. Flying commitments for unstable fighter aircraft deploying stability augmentation are brought out. Some aspects related to data generation through wind tunnel testing and flight simulation are highlighted. Flight test points for the flight envelope expansion and related criterion are explained. Fault tolerant flight control system testing is covered. The aerodynamic considerations are largely dealt herein for the purpose of flight envelope expansion for the prototype fighter programs.