Obviously, all concept of any aircraft is a compromise between conflicting requirements. Performance improvements generally induce direct cost.
KeywordsCombustion Entropy Vortex Enthalpy Peru
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- (1).Dassault Aviation report 1.11.34 Winglet-vertical tail choice for HermesGoogle Scholar
- (2).Allen H. Whitehead, “Nasp Aerodynamics”. AIAA First National Aerospace Plane Conference, Paper n° 89–5013, Dayton, OH, July 20–21 1989.Google Scholar
- (3).David H. Campbell, “F-12 series aircraft propulsion system performance and development”, AIAA 5th Aircraft Design, Flight Test and Operations Meeting, Paper n° 73–821, St Louis, Missouri, August 6–8, 1973.Google Scholar
- (4).M. Rigault, “A Methodology for the Concept Definition of Advanced Space Transportation Systems”, conference EAC 89, Bonn-Bad Godesderg, 23 may 1989.Google Scholar
- (5).Wolfgang Schmidt “Aerodynamics of High Speed Air Intakes”, Status Report on FDP— WG13 Agard Pep 75th Symposium Madrid — May 1990.Google Scholar
- (6).M. Mallet, J. Periaux, P. Perrier, B. Stoufflet, “Flow Modelization and Computational Methodologies for the Aerothermal Design of Hypersonic Vehicles: Application to the European Hermes”. AIAA Thermophysics, Plasma dynamics and lasers conference, Paper n° 88–2628, San Antonio, Texas, June 27–29, 1988.Google Scholar
- (7).M. Mallet, J. Periaux and G. Roge, “Development of Finite Element Methods for Compressible Navier Stokes Flow Simulations in Aerospace Design”. AIAA Aerospace Sciences Meeting, Paper n° 90–0403, Reno, Nevada, January 8–11, 1990.Google Scholar
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