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2 Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2 2001

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Flight test investigations of aerodynamic features of the manoeuvrable jet trainer YAK/AEM-130

Matveev A., Popovich K.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 12

1-6

To investigate some special aerodynamic features of the new manoeuvrable Jet Trainer Yak/A EM-130 Demonstrator (see Fig. 1) unique flight tests were performed in the years 1999(1) and 2000. The aircraft is equipped with the two PSLM DV-2 turbofan engines, each of them being rated at 2200 kg, and the normal take off weight of the aircraft is 7000 kg. The aerodynamic configuration is characterised by the moderate aspect ratio wing equal to 4 and the leading edge swept angle equal to 31 deg. with a camber changmg by means of leading and trailing edge flaps and strakes optimised for medium and high angles of attack (AOAs). The aircraft presents some interesting design features: the maximum design AOA=40 deg., capability of combining operational characteristics common to modern fighters; such as the optimum point performance speed at M=0.75-0.8 and the low speed performance typical for a basic trainer. The aircraft was built at the Yakovlev Design Bureau and it is on a flight test stage now. The AOA envelope including AOAs up to 42 deg. for a speed up to M=0.4 and AOAs up to 15 deg. for M=O.85 has been investigated. The paper presents some results of the aerodynamic investigations, which were necessary for solving the problems appearing during flight tests.

A new method for agile aircraft stability evaluation

Pietrucha J., Sibilski K.

Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics

2001

nr 12

39-44

In the paper a study of high angle of attack dynamics of an advanced trainer aircraft is presented. This dynamics is non-linear, therefore the theory of dynamical system (TDS) approach can be useful in the analysis. The equations of motion used in this investigation assume a rigid aircraft with movable control surfaces. Aerodynamic forces and moments found in equations of motion are valid for a region of higher angles of attack including deep stall phenomena. Results obtained from the TDS are used to predict the nature of the instabilities caused by the bifurcations and the response of the aircraft after a bifurcation is studied. Based data for the MiG29 fighter aircraft are used.