Master of Science in Aerospace Systems Engineering (MSASE), Wright State University, 2021, Mechanical Engineering
The dual-plane airfoil has been adopted in the design of aircraft wings, wind turbine blades, and propellers. The purpose of this research is to investigate the most important design parameters of a dual-plane airfoil model for the best aerodynamic performance, such as gap, stagger, and decalage. The dual-plane airfoil model was designed using the S826 profile. A mechanical mechanism with electrical actuator control is particularly designed to alter the gap and stagger smoothly, as well as the angle of attack (AOA) for each airfoil. It results in a gap range of 1.38c to 2.17c, a stagger range of -0.75c to 1.75c (c is the chord length), an AOA range of -10 to 20 degrees. The decalage angles of 0, 1, and 2 degrees are adopted in the tests for AOA=12 degrees. A low-speed open-circuit wind tunnel at Wright State University is used for the experiment at two Reynolds numbers, 𝑅𝑒=60000, and 𝑅𝑒=100000, respectively. Both airfoils are equipped with 21 pressure tap holes around the airfoil in the middle section. Pressure distribution data around the airfoil is sampled at a rate of 400 Hertz using the DSA 3217 Pressure Scanner. The collected data is processed to calculate the pressure coefficient on the surface of both airfoils. The pressure distribution profiles are generated and compared at various gaps, staggers, and decalages. Lift and drag coefficients are calculated by integrating the pressure distribution over the airfoil. It has been found that both stagger and gap have a significant effect on the pressure distribution at AOA of 12 degrees for the bottom airfoil. A gap ranges from 1.38c to 1.57c can suppress the separation and increase the lift coefficient of the top airfoil at various staggers and decalages. A stagger of 1.75c and negative staggers at a gap of 1.38c can suppress the separation and increase the lift coefficient of the bottom airfoil. Due to boundary layer separation, negative staggers are not effective for 𝑅𝑒=60000. The decalage effect is distinct at (open full item for complete abstract)
Committee: Zifeng Yang Ph.D. (Advisor); Jim Menart Ph.D. (Committee Member); Junghsen Lieh Ph.D. (Committee Member)
Subjects: Aerospace Engineering; Mechanical Engineering