Skip to Main Content
 

Global Search Box

 
 
 
 

Files

File List


AHussain_MS_THESIS_Final.pdf (5.18 MB)

ETD Abstract Container

Abstract Header

The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance

Hussain, Ali
http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

Abstract Details

2019, Master of Science, Ohio State University, Aero/Astro Engineering.
Active flow control (AFC) in the form of a wall normal slot was investigated on a NACA 643-618 laminar wing model. The wing model has a leading-edge sweep of (Λ = 30°) and tests were performed using a chordwise Reynolds number of 100,000 with a specific focus on the stall characteristics and changes in performance of an AFC slot with spanwise location. The study included comparing a passive boundary layer fence (BLF) and an AFC slot at the same spanwise locations: 0.60z/b, 0.70z/b, and 0.80z/b. Changing the location of the passive BLF resulted in increases in the maximum lift coefficient (CLMax) over the baseline ranging from 10.20-19.30%, with higher gains seen for fences closer to the root. The BLF at 0.60z/b experienced an unstable longitudinal static stability derivative (CMα) at an angle 13° higher than the baseline. Moving the fence outboard to 0.80z/b resulted in delaying this unstable behavior by an additional α=6°. An AFC slot was found to improve upon aspects of the BLF performance at all spanwise locations tested for a Cμ=10.33%. The slot was found to improve CLMax by up to 23.4% at the lowest spanwise location tested (0.60z/b) and this decreased to a 10.6% benefit at 0.80z/b. For the AFC slot, maximum lift performance increased monotonically as more momentum was introduced into the system. In all cases, moving the slot further outboard increased the stall angle. At all spanwise locations, the AFC slot outperformed the BLF in terms of delaying stall and an unstable CMα. Fluorescent tufts were used to visualize the surface flow for the baseline and AFC at all spanwise locations. The results corroborated the load cell findings and helped to visualize separation and spanwise flow at key angles of attack such as stall for the baseline wing. At higher angles of attack, evidence of the AFC slot could clearly be seen in the attached, streamwise flow directly outboard of the fence location. Evidence of a fence and tip vortices were also present for the AFC configurations, explaining the increased lift benefits seen.
Jeffrey Bons (Advisor)
James Gregory (Committee Member)
91 p.
Aerospace Engineering
aerodynamics; active flow control; boundary layer fence; swept wing; experimental; wind tunnel

Recommended Citations

Citations

  • Hussain, A. (2019). The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance [Master's thesis, Ohio State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

    APA Style (7th edition)

  • Hussain, Ali. The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance. 2019. Ohio State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521.

    MLA Style (8th edition)

  • Hussain, Ali. "The Effect of Spanwise Location of an Active Boundary Layer Fence on Swept Wing Performance." Master's thesis, Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1555516043121521

    Chicago Manual of Style (17th edition)

osu1555516043121521
1,415
© 2019, all rights reserved.
This open access ETD is published by The Ohio State University and OhioLINK.