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- Type of Document: M.Sc. Thesis
- Language: Farsi
- Document No: 49677 (45)
- University: Sharif University of Technology
- Department: Aerospace Engineering
- Advisor(s): Soltani, Mohammad Reza
- Abstract:
- In this experimental study, a series of wind tunnel tests were performed to examine the wake flow profile over three swept wings with sweep angles of 23, 33 and 40 degrees with similar aspect ratio at various conditions. The airfoil of wing was a NACA 6-series airfoil designed to provide a laminar flow on the front half of the airfoil. The tests, made at a mid aerodynamic chord Reynolds number of 8×〖10〗^5, covered an angle of attack range of -2 to 10 degree. The wing tip vortex effects are eliminated by placing an End-plate on the wing tip.The tests were carried out at two main section of wing and two various position from behind of wing. A total pressure rake and transducers was used to measure the wake flow profile indeed velocity of wake. The obtained data of wake flow analyzed by wake survey method and achieved the drag coefficient for two sections of models. Study on the results of drag coefficients indicate that the drag coefficient for the high sweep angle wing less than the other wings. Actually, the wings with lower swept in the high angles of attack has sudden increase of the drag coefficient. The greater effects of sweep angles is more obvious with increasing angle of attack. The power spectrum analysis was performed for all wings and cases, the frequency range 6 Hz is the dominant peaks. This frequency seems to be associated with the cross flow instability. The amplitude of this frequency decreases as the angle of attack increases
- Keywords:
- Drag Coefficient ; Spectral Analysis ; Frequency Analysis ; Sweep Angle ; Inlet Guide Vane ; Two Dimentional Wing ; Wake Survey Method ; Wake Flow
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