The mathematical models and data used in the off-line flight simulation of the rotodomed aircraft have been described in detail in Part 1 . The issues related to the Rolls Royce Engine simulation studies have been presented in Part 2 . In this document, static wind tunnel test data generated at H .A .L and considered as acceptable by BAE has been used as a reference data for verifying and formulating the aero-static model and associated data for HS-748 and AEW configurations . The resulting static model has been combined with dynamic model to arrive at an overall representative Aero model for use in flight simulation studies . This procedure is vital for unusual aircraft configurations as most of the data at design stage is available only from static wind tunnel tests
