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

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Aerodynamic design features of the strafer Su-25

Babak V., Chernov L.

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

2001

nr 11

13-16

On 22 February, 2000 there was the 25th anniversary of the Su-25 strafer maiden flight. Over the years since being designed the Su-25 has proved to be a highly-effective close air support aircraft capable of executing combat missions with the employment of gun and bombs under severe counter-air firing, even in mountainous areas. Nowadays the Su-25 aircraft (Fig.1) are employed in many countries, being involved in regional conflicts. The aircraft proved again its high combat effectiveness. The mission success depends greatly on the aircraft manoeuvrability. Owing to perfection of the aerodynamic design the Su-25 is a highly manoeuvrable aircraft that affords reliability and survivability when flying combat missions.

Optimization of aerodynamic design of human powered helicopter

Popela R.

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

1999

nr 9

207-210

This paper deals with the application of genetic algorithm as an optimization technique to the aerodynamic design of helicopter rotor. A special kind of helicopter, human powered helicopter, is optimized as a test case. The main result of this work is a development of aerodynamic optimization tool for helicopter rotors and propellers.

Zaero: a unified AIC module for aerodynamic/aeroelastic design and analysis

Chen P., Sarhaddi D., Liu D.

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

1998

nr 8

103-122

The ZAERO module is a unified unsteady/steady aerodynamic influence coefficient (UAIC) methodology for complex aircraft configurations which is applicable to all Mach numbers covering the unified subsonic, transonic, supersonic and hypersonic ranges. Various application examples in using ZAERO for unsteady pressure and flutter analysis and for wing structural design/optimization are presented. The stand-alone ZAERO has a versatile program structure in that it can readily be interfaced with existing FEM programs such as NASTRAN or ASTROS for aerodynamic/aeroelastic design and analysis. Seamlessty integrated with ASTROS, ZAERO is now the newly adopted aerodynamic module to replace the DLM/CPM and USSAERO for dynamic/static aeroelasticity applications within the ASTROSIMDO environment. Meanwhile, the development of an aeroservoelastic (ASE) module based on ZAERO is near completion. Almost all results obtained for the above examples show favorable comparisons with available data, thus demonstrating the capability and solution accuracy of ZAERO. While the releases of ZAERO and ASTROS* (^ZAERO+ASTROS) are forthcoming, the validation of the ZAERO/ASE module is aggressively being pursued at present.