A wind tunnel model of a SST(Supersonic Transport) arrow wing was tested in transonic regime. The purpose of this experiment is to accumulate verification data for the establishment of aeroelasticity related CFD codes and ACT (Active Control Technology ) in the Japanese SST program. The model is a semi-span arrow wing with a fuselage. The leading edge is double-swept-backed as shown in Fig. 1 and 2. The inboard sections of the model was constructed mainly with 7 mm thickness aluminum plate. A NACAOOO3 airfoil was, then. shaped by urethane resin. The dimensionless coordinates are shown in Table 1. At outboard sections, the NACAOOO3 airfoil was directly manufactured by cutting down an aluminum alloy. The detailed information on the model fuselage is shown in Table 2. Table 6 shows the model's natural frequencies acquired by both FEM analysis and a vibration test. Figure 5 shows the contours of model natural modes acquired by FEM analysis.


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    Titel :

    NAL SST Arrow Wing with Oscillating Flap


    Beteiligte:
    M. Tamayama (Autor:in) / K. Saitoh (Autor:in) / H. Matsushita (Autor:in) / J. Nakamichi (Autor:in)

    Erscheinungsdatum :

    2000


    Format / Umfang :

    24 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






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