| Calculation of the Aerodynamic Tail Loads for NALLA (1991) | |||||||||||||
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| PD National Aeronautical Laboratory Calculation the Aerodynamic Tail Loads for LLA ASHOK Flight Experiments Division Project Document October Bangalore India iwtarm uai fib ABSTRACT The aerodynamic loads the tail surfaces for NALLA have been estimated using FAR Part The methods used and the results obtained are presented NOMENCLATURE n pitching moment coeffecient total total lift lift load both sides the horizontal load the wing tail load factor flight velocity Subscripts for acondition the flight envelope condition the flight envelope condition the flight envelope reference axes Refer fig Airplane Fuselage station Butt line Water line INTRODUCTION the For the purpose structural design and analysis have the horizontal and vertical tails aerodynamic loads CFAR Requirements calculated The Federal Aviation used for these calculations and this Part Cref has been report documents the methods used and the results obtained light airplane The NALLA two seat single engine the three view Figure shows designed trainer being the details for airplane The important drawing the table The detailed drawings for the airplane are listed and and vertical tails are shown figs horizontal respectively can seen has pod and boom type construction this design the tail boom attached This fuselage which turn attached the the wing becomes very important the tail loads will have factor the considered not only when analysing the tail surfaces the wingboom and the boom wing attachment but also for fuselage | |||||||||||||
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