Flight envelope protection using flap hinge moment measurement

Ansell, Phillip J.

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https://hdl.handle.net/2142/16147 Copy

Description

Title

Flight envelope protection using flap hinge moment measurement

Author(s)

Ansell, Phillip J.

Issue Date

2010-05-19T18:38:55Z

Director of Research (if dissertation) or Advisor (if thesis)

Bragg, Michael B.

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois at Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• hinge moment
• envelope protection
• icing
• simulated icing
• roughness
• simulated damage
• contamination
• Aerodynamics
• aeronautics
• stall
• NACA 3415
• NACA 23012
• glaze ice
• rime ice
• trim tab
• Flap
• control surface

Abstract

An experimental investigation of the sensitivity of flap hinge moment to airfoil surface contamination was conducted at the University of Illinois at Urbana-Champaign Aerodynamics Research Lab. Tests were conducted on two airfoil models, an NACA 3415 and an NACA 23012, at Reynolds numbers of 1.8 × 106 and 1.0 × 106. The effects of six different simulated contamination configurations on the performance characteristics of both airfoils were tested. These configurations consisted of glaze ice, rime ice, two severities of distributed leading-edge roughness, three-dimensional leading-edge damage, and three-dimensional upper-surface damage. Additionally, the effects of flap deflection and trim tab deflection on the unsteady hinge moment were studied. Results from this study found that large increases in Ch.StDev often occurred at the same angle of attack as Cl,max. By correlating regions of separated flow observed in Cp distributions and fluorescent-oil flow visualizations to Ch,StDev at discrete angles of attack, it was determined that regions of boundary-layer separation were the primary driver for large increases in unsteadiness in the hinge moment. It was also found that the unsteady hinge moment had negligible dependence on trim tab deflection. The response of Ch,StDev was dependent on the stalling characteristics of the airfoil model. Of all of the contamination configurations tested, the two simulated ice cases had the largest effect on the performance of the airfoils. For the distributed leading-edge roughness cases, the larger roughness elements had a larger effect on the performance than the smaller roughness elements, but the Ch,StDev response of both roughness cases were comparable. While the 3D simulated damage cases did not significantly affect the lifting characteristics of either model, the magnitude of the Ch,StDev response of the 3D simulated damage case was comparable to the 2D contamination cases. Additionally, the large increase in Ch,StDev occurred prior to stall due to localized regions of separated flow that resulted from the simulated damage.

Graduation Semester

2010-5

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http://hdl.handle.net/2142/16147

Copyright and License Information

© 2010 by Phillip J. Ansell

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