The drag level is a major element to be determined, especially in flight conditions (i.e. at the flight Reynolds number value), in order to assess the final aircraft performance. Aerospatiale, as the partner in charge of engine integration, have to provide Airbus Industry with the engine installation drag. In fact, it also means to propose corresponding experimental tools and dedicated numerical methods. The Aerospatiale cryogenic model program, which is underway within the French Official Services support, was initiated to develop the technology for design and manufacturing of cryogenic models for ETW (European Transonic Windtunnel). In particular, in order to check the feasibility of obtaining the effects of the installation in conditions similar to the flight ones, together with a databank for developing calculation codes, the third phase of the French Civilian Program is dedicated to the simulation of propulsion. The first model for this propulsion effect study will be a 1/24th scale reference half-model of a A330/A340 aircraft fitted with two through flow nacelles (TFN) or two cryogenic simulators (TPS - Thermal Protection Systems) of 76 mm diameter fan; thus, the model and the simulators are designed to be used within the ETW envelope in cryogenic conditions (Ti = 120 K; Pi = 3 bar). A brief overview of the Aerospatiale cryogenic model is presented in this paper. The points that will be focused are the simulator technology and the proposed Aerospatiale cryogenic test technic using, particularly, a dedicated cryogenic calibration bench facility, in order to obtain the thrust of the powered simulators and through flow nacelles with a great accuracy.


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    Title :

    Cryogenic TPS test technic


    Additional title:

    Kryoprüftechnik für Wärmeschutzsysteme (TPS)


    Contributors:
    Rollin, C. (author) / Icart, G. (author)


    Publication date :

    1997


    Size :

    14 Seiten, 14 Bilder



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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