... as actively controlled surfaces to improve the performance of aircraft at various flight conditions and to “tune” the longitudinal stability characteristics of the configuration. 12 09 2007 16 03 2008 02 07 2008 aerodynamics aerospace components aircraft drag reduction wakes wind...

...Edward B. White; Jason A. Schmucker Predicting the runback threshold for liquid drops in aerodynamic boundary layers is a challenging problem with numerous applications including aircraft icing simulations. The critical parameters that govern drop runback are investigated in this experiment...

... turbulence flow visualisation turbines compressors aircraft S-duct diffusers are specially designed inlets through which air is taken from the external flow and supplied to the engines of a combat aircraft. Hence these diffusers form a vital component of any air breathing engine. The use...

...Michael J. Brear; Jack L. Kerrebrock; Alan H. Epstein This paper discusses the requirements for the propulsion system of supersonic cruise aircraft that are quiet enough to fly over land and operate from civil airports, have trans-pacific range in the order of 11,112 km ( 6000 nmi ) , and payload...

... 06 October 2003 03 05 2004 aircraft aerospace engines flow separation aerodynamics The engine inlets of uninhabited combat air vehicles (UCAV’s) are often serpentine. Furthermore, the structural weight of UCAV’s is minimized by making the inlet as short and as narrow...

... due to the physical limits these phenomena impose on aircraft and missiles at extreme flight conditions. Demands for more maneuverable air vehicles have pushed the limits of current CFD methods in the high Reynolds number regime. Simulation methods must be able to accurately describe the unsteady...

.... , 1988 , “ Unsteady Low-Speed Aerodynamic Model for Complete Aircraft Configurations ,” J. Aircr. , 25 ( 4 ), pp. 302 – 310 . Romanowski, M. C., 1995, “Using Fluid Eigenmodes to Develop Euler Based Reduced Order Unsteady Aerodynamic and Aeroelastic Models,” PhD. thesis, Duke University, Durham, NC...

... months of computing. Improvements in computer power, largely through massive parallelization, have already demonstrated turn-around times on the order of a few weeks for the separated flow behind an F15 and F16 aircraft (J. Forsythe, personal communication, 2001). Turn-around times...

... 24 August 2001 aerodynamics flow control aircraft boundary layers vortices flow separation In Fig. 6 , centerline C p distributions of bare diffuser1 and 2 are presented together with their most optimum configurations of fences and vortex generators...

... generic airfoil with 4 percent Gurney fitted at α = 0   deg , δ f = 20 and 50 deg Liebeck , R. H. , 1978 , “ Design of subsonic airfoils for high lift ,” AIAA J. Aircraft , 15 , No. 9, Sept., pp. 547 – 561 . Papadakis, M., Myose, R. Y., Heron, I...