The present paper deals with the design loop and aerodynamic analysis of a MALE (Medium Altitude Long Endurance) UAV. Starting from the mission specification, requirements and mission profile, weights estimation and design match point analysis have been performed. From this preliminary work the needed values of wing-loading and power-to-weight ratio have been identified and the required wing area and engine power have been estimated. The global configuration has been chosen taking into account the payload and the rear engine installation requirement. A wing section optimization was performed trying to maximize the endurance parameter CL3/2/CD with a limited increase of the pitching moment coefficient since high value of airfoil pitching moment leads to high tail loads to balance the aircraft with consequent high trim drag and loss of efficiency. A complete analysis of global aircraft performances has been performed and the effect of moment coefficient on global aircraft drag and endurance has been evaluated.
Design, aerodynamic analysis and performances estimation of a MALE Turbo-Prop UAV for civil application / Coiro, Domenico; Nicolosi, Fabrizio; Genito, Nicola; G., Andreutti. - ELETTRONICO. - (2004), pp. 1-10. (Intervento presentato al convegno 4° International Conference on Advanced Engineering Design tenutosi a Glasgow (UK) nel 5-8 September 2004).
Design, aerodynamic analysis and performances estimation of a MALE Turbo-Prop UAV for civil application
COIRO, DOMENICO;NICOLOSI, FABRIZIO;GENITO, NICOLA;
2004
Abstract
The present paper deals with the design loop and aerodynamic analysis of a MALE (Medium Altitude Long Endurance) UAV. Starting from the mission specification, requirements and mission profile, weights estimation and design match point analysis have been performed. From this preliminary work the needed values of wing-loading and power-to-weight ratio have been identified and the required wing area and engine power have been estimated. The global configuration has been chosen taking into account the payload and the rear engine installation requirement. A wing section optimization was performed trying to maximize the endurance parameter CL3/2/CD with a limited increase of the pitching moment coefficient since high value of airfoil pitching moment leads to high tail loads to balance the aircraft with consequent high trim drag and loss of efficiency. A complete analysis of global aircraft performances has been performed and the effect of moment coefficient on global aircraft drag and endurance has been evaluated.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
