The influence of a rotating leading edge on accelerating starting flow over an airfoil

F. Finaish, R. W. Jefferies

Research output: Contribution to conferencePaperpeer-review

Abstract

This study reports an experimental investigation on the influences of a rotating leading edge on vortex developments over an airfoil uniformly accelerated from rest. To evaluate such flow, a NACA 0015 airfoil that incorporates a rotating leading edge was subjected to a nearly constant acceleration of 2.4 m/sec2 after start from rest. Flow visualization technique of direct injection of liquid titanium tetrachloride was employed to visualize the flow developments over the airfoil. The study demonstrates the roli of the leading edge rotation in controlling flow separation and subsequent vortex development for an angle of attack range between 10“and 30°. The results suggests that the concept of the rotating leading edge may be utilized to control the characteristics of unsteady separated flows over lifting surfaces. This control possibility seems to be quite effective and could have significant consequences for future applications in controlling unsteady separated flows.

Original languageEnglish (US)
StatePublished - Jan 1 1990
Event28th Aerospace Sciences Meeting, 1990 - Reno, United States
Duration: Jan 8 1990Jan 11 1990

Other

Other28th Aerospace Sciences Meeting, 1990
CountryUnited States
CityReno
Period1/8/901/11/90

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

Fingerprint Dive into the research topics of 'The influence of a rotating leading edge on accelerating starting flow over an airfoil'. Together they form a unique fingerprint.

Cite this