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Keywords: aircraft
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Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Fluids Eng. July 2008, 130(7): 071103.
Published Online: July 2, 2008
... 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...
Journal Articles
Publisher: ASME
Article Type: Research Papers
J. Fluids Eng. June 2008, 130(6): 061302.
Published Online: May 19, 2008
...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...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. November 2006, 128(6): 1192–1203.
Published Online: May 5, 2006
... of flow control used here is perceived to have applications in turbomachinery like turbines and compressors. 24 02 2006 05 05 2006 flow control flow separation vortices jets boundary layer turbulence flow visualisation turbines compressors aircraft S-duct diffusers...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. March 2006, 128(2): 370–377.
Published Online: March 8, 2005
...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...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. March 2004, 126(2): 266–272.
Published Online: May 3, 2004
... of results bears this out. Figure 2 shows the area averaged inlet pressure recovery versus the inlet mass-flow rate. The inlet pressure recovery is reasonable at the design mass-flow rate of 3.13 lb/s (Table 1 ), although it is roughly 2% below the pressure recovery of current, civil aircraft engine...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. December 2002, 124(4): 924–932.
Published Online: December 4, 2002
... 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...
Journal Articles
Publisher: ASME
Article Type: Additional Technical Papers
J. Fluids Eng. December 2002, 124(4): 988–993.
Published Online: December 4, 2002
... equations aircraft Reduced-order modeling is a conceptually novel and computationally efficient technique that is recently used in analysis of unsteady flows. Unsteady flow eigenmodes are used to construct reduced-order unsteady flow models similar to the normal mode analysis in structural dynamics...
Journal Articles
Publisher: ASME
Article Type: Additional Technical Papers
J. Fluids Eng. June 2002, 124(2): 413–423.
Published Online: May 28, 2002
... . Manuscript received by the Fluids Engineering Division July 23, 2001; revised manuscript received January 24, 2002. Associate Editor: T. Gatski. 23 July 2001 24 January 2002 28 05 2002 aerodynamics aircraft flow separation Navier-Stokes equations aeroacoustics noise abatement...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. March 2002, 124(1): 136–142.
Published Online: August 24, 2001
... 24 August 2001 aerodynamics flow control aircraft boundary layers vortices flow separation Combat aircrafts have one or two engines, which are generally integrated with the fuselage. Supplying them with the necessary quantity of air for generating thrust takes place by means...
Journal Articles
Publisher: ASME
Article Type: Technical Papers
J. Fluids Eng. March 2001, 123(1): 99–104.
Published Online: August 28, 2000
.... 03 February 2000 28 August 2000 aerodynamics flow control wakes vortices pressure measurement aircraft By fitting a short strip perpendicular to the pressure-surface trailing-edge of a wing it is possible to increase both the C L generated at a given incidence...