Skip to Main Content
 

Global Search Box

 
 
 
 

Files

File List


Rhodes_Master_Thesis.pdf (3.05 MB)

ETD Abstract Container

Abstract Header

Experimental Investigations of the Propulsive Fuselage Concept

Rhodes, Gregory D
http://rave.ohiolink.edu/etdc/view?acc_num=osu1523355985000317

Abstract Details

2018, Master of Science, Ohio State University, Aero/Astro Engineering.
Air traffic across the globe is expected to increase dramatically by the year 2035, with nearly twice as many passengers as compared to 2016 [1]. Such an increase in air travel demand will necessarily require a surge in daily flights, forcing aviation efficiency and ecology to escalate in priority. The "Propulsive Fuselage" is one concept that could lead the way in this effort. Theory suggests that a fan located on the aft end of a traditional, commercial fuselage can improve the efficiency of the podded engines beneath the wing by re-accelerating the boundary layer. The re-energizing of the fuselage boundary layer would reduce the velocity deficit in the aircraft wake, ultimately reducing the thrust required for straight and level flight as well as reducing energy consumption. Presently, there is considerable lack of experimental data in understanding this concept. Therefore, a model fuselage-propulsor integration was constructed to obtain the aerodynamic characteristics along the fuselage in addition to obtaining the performance of the propulsor. Three fuselage models with varying inlet ramp angles were tested in dynamic conditions over a range of freestream velocities. The analysis was conducted at the Aerospace Research Center at The Ohio State University in Columbus, Ohio with the use of a 3’ x 5’ Eiffel Type Subsonic Wind Tunnel. The simulated propulsor was a 1/6th scale model of a 2,000 lbf thrust class engine. The engine simulator used a high pressure, ejector driven system. These systems are beneficial as they are mechanically simple, requiring no moving parts. The five degree model demonstrated the lowest inlet distortion percentage overall, but did not indicated any significant increase in boundary layer velocity with BLI active. The ten and fifteen degree models did show an increase in the velocity of the boundary layer, but had larger inlet distortion percentages. The ten-degree model did not indicate separated flow, whereas the fifteen-degree model did. The ten-degree model should be further investigated. The tests performed have contributed to the experimental database for propulsor-fuselage concepts.
Clifford Whitfield (Advisor)
Richard Freuler (Committee Member)
71 p.
Aerospace Engineering
drag ingestion; propulsive fuselage;

Recommended Citations

Citations

  • Rhodes, G. D. (2018). Experimental Investigations of the Propulsive Fuselage Concept [Master's thesis, Ohio State University]. OhioLINK Electronic Theses and Dissertations Center. http://rave.ohiolink.edu/etdc/view?acc_num=osu1523355985000317

    APA Style (7th edition)

  • Rhodes, Gregory. Experimental Investigations of the Propulsive Fuselage Concept. 2018. Ohio State University, Master's thesis. OhioLINK Electronic Theses and Dissertations Center, http://rave.ohiolink.edu/etdc/view?acc_num=osu1523355985000317.

    MLA Style (8th edition)

  • Rhodes, Gregory. "Experimental Investigations of the Propulsive Fuselage Concept." Master's thesis, Ohio State University, 2018. http://rave.ohiolink.edu/etdc/view?acc_num=osu1523355985000317

    Chicago Manual of Style (17th edition)

osu1523355985000317
347
© 2018, all rights reserved.
This open access ETD is published by The Ohio State University and OhioLINK.