...-mounted on the upper surface of the aircraft (Fig. 3 ), the boundary layer ingested into the inlet will be closely affected by its bottom wall but not the top wall. This assertion is supported by the results to be shown later, as the boundary layer on the top wall, which begins at the inlet highlight...

... and performance assessment methodology for advanced propfan powered aircraft configurations. The approach is based on first principles and combines a coupled aircraft and propulsion system mission and performance analysis tool with 3D unsteady, full-wheel CRP computational fluid dynamics computations...

...N. D. Cardwell; P. P. Vlachos; K. A. Thole Gas turbines for aircraft are designed for operation with a clean inlet air flow. This ideal operational condition is often violated during take-off and landing, where the probability of particle ingestion is high, with sand and dirt being the most...

.... , 1987 , “ Secondary Flow, Turbulent Diffusion and Mixing in Axial-Flow Compressors ,” J. Turbomach. 0889-504X , 109 , pp. 455 – 482 . 10.1115/1.3262127 Wisler , D. C. , 1988 , Advanced Compressor and Fan Systems, GE Aircraft Engines, Copyright. Wadia , A. R. , and Beacher...

... injected into industrial compressors for purposes of power augmentation. For that matter, They were mainly interested in the effects of aircraft compressors on runway approach during heavy rainstorms. Hence, it is reasonable to assume that at much lower levels of injection typical of application...

...George Kopasakis; Joseph W. Connolly; Daniel E. Paxson; Peter Ma Under the NASA Fundamental Aeronautics Program, the Supersonics Project is working to overcome the obstacles to supersonic commercial flight. The proposed vehicles are long, slim body aircrafts with pronounced aeroservoelastic modes...

...P. N. Shah; D. D. Mobed; Z. S. Spakovszky A novel air-brake concept for next-generation, low-noise civil aircraft is introduced. Deployment of such devices in clean airframe configuration can potentially reduce aircraft source noise and noise propagation to the ground. The generation of swirling...

... loss, and to obtain data of Nusselt number and pressure loss coefficient for the design of turbine nozzles in the future by applying this new cooling structure to next-generation small-class aircraft engines. Additionally a preliminary analysis of airfoil cooling was performed to evaluate both cooling...

..., new aircraft engines tend to have low pressure turbines with blades that have a reduced chord. This adds to the significance of the separation bubble in terms of the profile loss and the problems of controlling this with wakes alone. At the same time there is a growing interest in high altitude...

.... , 1969 , “ Discharge Coefficients for Thick Plate Orifices With Approach Flow Perpendicular and Inclined to the Orifice Axis ,” NASA Technical Report No. TN D-5467. 26 08 2008 01 03 2009 05 04 2010 05 04 2010 aerospace components aircraft design engineering durability...

... conditions, and particles present in clouds, during in-flight conditions, are the primary sources of particle ingestion for aircraft turbine engines. Blockages from these particles in these cooling passages reduce the effectiveness of cooling by decreasing the coolant flow rate, and subsequently part life...

...Michael Flouros Advanced aircraft engine development dictates high standards of reliability for the lubrication systems, not only in terms of the proper lubrication of the bearings and the gears, but also in terms of the removal of the large amounts of the generated heat. Heat is introduced both...

... to in the research community. The case histories of two projects are given to illustrate the point: the development of the concept of “smart jet engines” and the Silent Aircraft Initiative. In addition to providing a capability to attack multidisciplinary problems, the way in which collaboration can enhance...

... , “ Compressor Stability and Control: Review and Practical Implications ,” Proceedings of the RTO AVT Symposium 51 on Active Control Technology for Enhanced Performance Operational Capabilities of Military Aircraft, Land Vehicles and Sea Vehicles , Braunschweig, Germany. Kefalakis , M. , and Papailiou...

...Cesare A. Hall; Daniel Crichton The Silent Aircraft Initiative is a research project funded by the Cambridge-MIT Institute aimed at reducing aircraft noise to the point where it is imperceptible in the urban environments around airports. The propulsion system being developed for this project has...

...Daniel Crichton; Liping Xu; Cesare A. Hall Preliminary fan design for a functionally silent aircraft has been performed with noise reduction as the primary goal. For such an aircraft the fan design must, in addition to delivering low cruise fuel burn, enable low jet and fan source noise during...

... February 2004 09 02 2005 jet engines aerospace propulsion turbines aircraft I was pleased and honored to be invited to make the opening presentation of the International Gas Turbine Institute Budugur “Bud” Lakshminarayana Memorial Session. It has been a privilege to know and work...

... condition. In a cruise condition, the aircraft is moving through stagnant air, creating a constant angle of flight relative to the incoming flow direction. In order to simulate angle of attack, additional boundary layer growth was required and an additional constant area section was installed ahead...

... aircraft boundary layer turbulence pressure control vortices rotors Few successful attempts have been made to reduce secondary loss through application of end-wall profiling to a blade row. One successful application of profiling has been demonstrated in the Linear Cascade at Durham University...

.... Paper No. 2002-GT-30186. Review Chair: E. Benvenuti. 03 June 2002 30 October 2001 23 01 2003 gas turbines aircraft heat transfer turbulence flow control pressure measurement temperature measurement Two competing desires for gas turbine engines are increased...