Wind-Tunnel Tests of Several Arrangements of External Auxiliary Fuel Tanks on a Fighter-Type Airplane

摘要

Tank arrangements tested were 350-gallon rectangular cross section tank attached directly to fuselage or wing and 150 or 300-gallon circular cross section tanks attached to wings or fuselage by single strut. Both rectangular directly attached tanks and circular single strut wing tanks proved impracticable. Circular 150 and 300-gallon fuselage-tank arrangements showed at least effect on aerodynamic characteristics. Tank angles of incidence and vertical distances from adjacent airplane surfaces had negligible effect.