Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles

Cengiz Camci, Nicholas Herwig, Ali Aktürk

Research output: Contribution to conferencePaper

Abstract

The ducted fan propulsion systems provide attractive solutions for manned and unmanned aerial vehicles, with potential applications in general aviation and military missions. They provide higher power-to-thrust ratios over their free-rotor counterpart. However, ducted fans currently implemented in vertical takeoff and landing (VTOL) type aerial vehicles have an inherent duct lip separation and inlet flow distortion problem in edgewise flight. This problem is severe when the flight direction of the VTOL vehicle and the rotor axis of rotation are normal to each other. Separation at the leading edge duct lip for this high angle of attack situation disallows flow from effectively entering the fan rotor causing unwanted inlet flow distortion. Discussed here will be optimized design solutions to controlling and/or eliminating this flow separation at the leading edge duct lip. The designed were three types of lip-s: parametric, detached duct lip, and double duct. The parametric lip-spoilers consisted of inner-face and outer-face duct lip-spoilers. Inner-face duct lip-spoilers predominantly contributed to increased control over the negative nose-up pitching moment while the outer face and detached duct lip-spoilers predominantly controlled the increase in the mass flow rate through the ducted fan rotor. The double-ducted fan (DDF) was successful in eliminating duct lip separation through its added second duct. The main purpose of this study is to design and test various duct lip-spoilers that improves the ducted fan aerodynamic performance in edgewise flight. The conceptual design, analysis and flow visualization for a number of novel lip-spoilers are discussed in detail.

Original languageEnglish (US)
StatePublished - Jan 1 2019
Event16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016 - Honolulu, United States
Duration: Apr 10 2016Apr 15 2016

Conference

Conference16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016
CountryUnited States
CityHonolulu
Period4/10/164/15/16

Fingerprint

Inlet flow
Flow separation
Takeoff
Landing
Ducts
Fans
Antennas
Rotors
Flow visualization
Angle of attack
Unmanned aerial vehicles (UAV)
Conceptual design
Aviation
Propulsion
Aerodynamics
Flow rate

All Science Journal Classification (ASJC) codes

  • Mechanical Engineering

Cite this

Camci, C., Herwig, N., & Aktürk, A. (2019). Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles. Paper presented at 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016, Honolulu, United States.
Camci, Cengiz ; Herwig, Nicholas ; Aktürk, Ali. / Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles. Paper presented at 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016, Honolulu, United States.
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Camci, C, Herwig, N & Aktürk, A 2019, 'Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles' Paper presented at 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016, Honolulu, United States, 4/10/16 - 4/15/16, .

Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles. / Camci, Cengiz; Herwig, Nicholas; Aktürk, Ali.

2019. Paper presented at 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016, Honolulu, United States.

Research output: Contribution to conferencePaper

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AU - Aktürk, Ali

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N2 - The ducted fan propulsion systems provide attractive solutions for manned and unmanned aerial vehicles, with potential applications in general aviation and military missions. They provide higher power-to-thrust ratios over their free-rotor counterpart. However, ducted fans currently implemented in vertical takeoff and landing (VTOL) type aerial vehicles have an inherent duct lip separation and inlet flow distortion problem in edgewise flight. This problem is severe when the flight direction of the VTOL vehicle and the rotor axis of rotation are normal to each other. Separation at the leading edge duct lip for this high angle of attack situation disallows flow from effectively entering the fan rotor causing unwanted inlet flow distortion. Discussed here will be optimized design solutions to controlling and/or eliminating this flow separation at the leading edge duct lip. The designed were three types of lip-s: parametric, detached duct lip, and double duct. The parametric lip-spoilers consisted of inner-face and outer-face duct lip-spoilers. Inner-face duct lip-spoilers predominantly contributed to increased control over the negative nose-up pitching moment while the outer face and detached duct lip-spoilers predominantly controlled the increase in the mass flow rate through the ducted fan rotor. The double-ducted fan (DDF) was successful in eliminating duct lip separation through its added second duct. The main purpose of this study is to design and test various duct lip-spoilers that improves the ducted fan aerodynamic performance in edgewise flight. The conceptual design, analysis and flow visualization for a number of novel lip-spoilers are discussed in detail.

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Camci C, Herwig N, Aktürk A. Inlet flow separation control via novel lip-spoilers for ducted fan based VTOL uninhabited aerial vehicles. 2019. Paper presented at 16th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC 2016, Honolulu, United States.