An aerodynamic characteristics identification method using dynamic flight tests was applied to an STOL experimental aircraft ''ASKA'' to identify a non-dimensional non-linear aerodynamic model for the experimental aircraft. The aircraft ''ASKA'' used in the tests has an aerodynamic specification of the wing width at 30.6 m, horizontal tail width at 11.3 m, and vertical tail width at 5.1 m. Static parameters of the identified aerodynamic model were compared with the results estimated from static or quasi-static flight tests, and the dynamic parameters with the results estimated theoretically based on the DATCOM method, the simple strip theory, and the independent tail calculation method. A non-linear computer simulation was carried out using the identified model as the basis, and the result was compared with the flight test record data. As a result, the effectiveness of the aerodynamic model identification using the dynamic tests was verified, except for some taking-off and landing patterns for which no sufficient test data have been obtained. 10 refs., 18 figs., 18 tabs.


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    Title :

    Teisoon STOL jikkenki 'ASKA' no doteki hiko shiken ni yoru kuriki model dotei. (Aerodynamic model identification of quiet STOL experimental aircraft 'ASKA' from dynamic flight test data)


    Publication date :

    1992


    Size :

    30 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English