... aircrafts: 23 A J + T L = i ( 2 π η ) [ ( L N + 1 2 L C Y L − C G N )   − ( K Y 2 − K X 2 )   ( C L A C M A ) ]   tan ⁡ ω   e i φ o Firing sidewise with V fir at an angle...

... the net total heat input is zero. 25 01 2008 07 05 2008 13 03 2009 aerospace propulsion aircraft finite element analysis heat pipes lithium alloys Mach number niobium alloys For aerodynamic reasons hypersonic vehicles require sharp leading edges, with millimeter...

... designed to operate isentropically over a Mach range from 2.5 to 3.8. The nozzle has been installed and operated in this Mach number range and the experimental results are presented. 10 09 2007 29 04 2008 11 03 2009 aerodynamics aircraft nozzles sandwich structures supersonic...

... in aircraft panel structures. This particular work considers an isotropic plate, typically made of aluminum, and containing a crack in the form of a continuous line with its center located at the center of the plate and parallel to one edge of the plate. The plate is subjected to a point load on its surface...