Performance of conventional helicopter configuration with wings

Ovaj diplomski rad bavi se temom performansi helikoptera konvencionalne konfiguracije sa krilima i utjecajem krila na performanse helikoptera. Na samom početku definirane su i usvojene geometrijske karakteristike rotora i helikoptera u odnosu na sličnu konfiguraciju helikoptera već u eksploataciji. S poznatim geometrijskim karakteristikama, razvijenom kombiniranom metodom teorije diska i elementarnog kraka iz literature, te testiranjem dostupnih modela rotora određene su aerodinamičke karakteristike glavnog rotora u vertikalnom i horizontalnom letu. Osim toga izvršena je procjena parazitskog otpora helikoptera u vertikalnom i horizontalnom letu, te je napravljena procjena koeficijenta sile uzgona krila. Time je moguće odrediti performanse helikoptera u standardnim režimima leta, ali isto tako i u jednom izvanrednom režimu leta helikoptera kod otkaza motora, autorotaciji. Pri analizi svih razmatranih performansi naglasak je na usporedbi rezultata konfiguracije sa i bez krila. S određenim koeficijentom sile uzgona krila, napravljena je korekcija pogonske sile u horizontalnom letu za konfiguraciju bez krila, te su dobiveni preliminarni iznosi kuteva mahanja, sila i momenata na glavi glavnog rotora.This Master's thesis deals with the subject of the helicopter's conventional wing configuration and their impact on the helicopter performance. At the very beginning the geometrical characteristics of the rotor and the helicopter were defined and adopted in relation to the similar known configuration of the helicopter in operational service. The aerodynamic characteristics of the main rotor in vertical flight were determined with developed combined momentum and blade element theory method and characteristics in the horizontal flight were determined by the available developed models. In addition, an estimate of the helicopter vertical and parasite drag in the vertical and forward flight was performed as well as wing lift coefficient. With all these data it was possible to determine the helicopter performance in standard flight procedures and flight regimes, but also with one emergency procedure, autorotation. In this thesis the emphasis is on comparison of selected performance results for configuration with and without wings. After wing lift coefficient was determined, it was used for correction of the thrust for configuration without wings, and preliminary results of flapping angle, force and moment at the main rotor hub were obtained