Application of CFD methods to propulsion system integration in the future supersonic transport aircraft

1997 ◽  
Author(s):  
D. Prat ◽  
T. Surply ◽  
D. Gisquet ◽  
D. Prat ◽  
T. Surply ◽  
...  
1967 ◽  
Vol 20 (1) ◽  
pp. 75-93
Author(s):  
P. Hugon

1. Preliminary consideration. In attempting to assess the worth of a navigation system already known, over against the demands of the supersonic transport aircraft, we shall take care above all to make no presumptions whatever regarding the future, and not to count on the developments of the transport aircraft as regards the favour it will find with its users and consequently with the airlines likely to put it into operation. The question is not put here as to whether the 3 to 1 reduction in the actual flying time will appear as a profit paying for the numerous other constraints which it will impose, at once on the constructors, on the operators and finally on the users, without counting the requirements regarding ground equipment and administrative agreements; the question is merely to know whether, given the normal flight and speed conditions of an aircraft, we have the means to navigate it in an accurate, safe and economical manner.


1991 ◽  
Vol 113 (1) ◽  
pp. 40-50 ◽  
Author(s):  
R. H. Tindell

The impact of computational fluid dynamics (CFD) methods on the development of advanced aerospace vehicles is growing stronger year by year. Design engineers are now becoming familiar with CFD tools and are developing productive methods and techniques for their applications. This paper presents and discusses applications of CFD methods used at Grumman to design and predict the performance of propulsion system elements such as inlets and nozzles. The paper demonstrates techniques for applying various CFD codes and shows several interesting and unique results. A novel application of a supersonic Euler analysis of an inlet approach flow field, to clarify a wind tunnel-to-flight data conflict, is presented. In another example, calculations and measurements of low-speed inlet performance at angle of attack are compared. This is highlighted by employing a simplistic and low-cost computational model. More complex inlet flow phenomena at high angles of attack, calculated using an approach that combines a panel method with a Navier-Stokes (N-S) code, is also reviewed. The inlet fluid mechanics picture is rounded out by describing an N-S calculation and a comparison with test data of an offset diffuser having massively separated flow on one wall. Finally, the propulsion integration picture is completed by a discussion of the results of nozzle-afterbody calculations, using both a complete aircraft simulation in a N-S code, and a more economical calculation using an equivalent body of revolution technique.


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