Flow control by spanwise blowing on a NACA 0012

Wong Chi, Konstantinos Kontis

    Research output: Chapter in Book/Report/Conference proceedingConference contribution

    Abstract

    Experimental studies were conducted on a NACA 0012 aerofoil section in a subsonic wind tunnel at a free stream Mach number equal to 0.035. The experiments examined the effect of spanwise blowing at different positions (0%, 25% and 100% of the chord-length of the aerofoil) for lift augmentation. The spanwise blowing is realized by injecting a high momentum jet in a direction across the span of the aerofoil. Measurements were done at a Reynolds number 1.25 × 105 based on the chord-length. Forces measurements using a three component balance were conducted to measure lift, drag and pitching moment for a range of angles of attack from -20 degrees to +20 degrees. The forces measurements of a NACA 0012 aerofoil with steady and unsteady blowing are compared with the aerofoil without blowing. The experimental results have shown that the lift generated on the NACA 0012 aerofoil with blowing is significantly higher than the aerofoil without blowing, while the drag is slightly increased. The most effective blowing location is found at 0.25c. The wake measurements were taken at a quarter chord length away from the trailing edge of the aerofoil section; the results show the effect of the added momentum from the blowing jet in the wake behind the aerofoil with steady blowing. Intensity spectrum analysis was conducted to investigate the level of fluctuations inside the wake. The flow patterns generated from both with and without steady blowing on the aerofoil were studied with the aid of oil flow visualization. The results suggest that the steady blowing jet has an effect on a portion of the aerofoil only due to the interactions with the on-coming freestream flow, which the blowing jet is deflected. The flow properties on the suction surface of the aerofoil were also studied using Hotwire Anemometry. The experiments demonstrated that application of spanwise blowing concepts on NACA 0012 aerofoil can be effective means of boundary layer control in subsonic flow.
    Original languageEnglish
    Title of host publicationCollection of Technical Papers - AIAA Applied Aerodynamics Conference|Collect. Tech. Pap. AIAA Appl. Aerodyn. Conf.
    Pages2215-2228
    Number of pages13
    Volume4
    Publication statusPublished - 2006
    Event24th AIAA Applied Aerodynamics Conference - San Francisco, CA
    Duration: 1 Jul 2006 → …

    Conference

    Conference24th AIAA Applied Aerodynamics Conference
    CitySan Francisco, CA
    Period1/07/06 → …

    Fingerprint

    Dive into the research topics of 'Flow control by spanwise blowing on a NACA 0012'. Together they form a unique fingerprint.

    Cite this