Newsletter  2019.3  Index

Theme : "The Conference of Fluid Engineering Division" Preface (T. HASHIMOTO，S. MATSUDA，H.J. PARK) Development and launch of sounding rockets and development status of small launch vehicle by Japanese startup company Takahiro INAGAWA (Interstellar Technologies Inc.) Experimental quantification of friction drag reduction effects on an airfoil using uniform blowing Kaoruko ETO, Yusuke KONDO, Koji FUKAGATA (Keio University)and Naoko TOKUGAWA (Japan Aerospace Exploration Agency) Wind-tunnel experiments of friction drag reduction on an airfoil using passive blowing Shiho HIROKAWA, Kaoruko ETO, Yusuke KONDO, Koji FUKAGATA (Keio University)and Naoko  TOKUGAWA (Japan Aerospace Exploration Agency) A Study on Airfoil Flow and Aerodynamic Noise with Wake-boundary layer Interaction Noriaki KOBAYASHI　(The University of Tokyo) LES Analysis of Stator Cascade Flow in a Transonic Axial Compressor Seishiro SAITO (Kyushu University) Influence of grid resolution in large-eddy simulation of a turbulent pipe flow using the WALE model Daiki IWASA, Yusuke NABAE, Koji FUKAGATA (Keio University) The Dreams of Flow Contest Tomomi TERADA (Hokkaido University)   Separation of floating waste by "Water Surface Control Device" Toshiki HOMMA　 (Meisei University)

 

Wind-tunnel experiments of friction drag reduction on an airfoil using passive blowing

Shiho HIROKAWA Keio University	Kaoruko ETO Keio University	Yusuke KONDO Keio University	Koji FUKAGATA Keio University	Naoko TOKUGAWA Japan Aerospace Exploration Agency

Abstract

Friction drag reduction effect of passive blowing on a Clark-Y airfoil is investigated experimentally. Passive blowing is driven by the pressure difference on the airfoil surface between the leading edge and the rear part of the upper surface, as shown in Fig. 1. The Clark-Y airfoil model actually built is shown in Fig. 2. A perforated metal plate with 0.5 mm diameter holes is used for the wing surface of suction and blowing regions. The experiment is performed using the 65 cm×55 cm low turbulence wind tunnel at Japan Aerospace Exploration Agency. The mean streamwise velocity profiles on the upper surface of the wing model were measured by a hot-wire anemometry at five streamwise locations. The Reynolds numbers based on the chord length are 0.65 × 10⁶ and 1.55 × 10⁶. The angles of attack are set to 0° and 6°. The streamwise mean velocity profiles in the blowing region and the downstream, shown in Fig. 3, are found to be shifted away from the wing surface. This behavior qualitatively suggests reduction of the velocity gradient on the wing surface, which indicates the friction drag reduction effect of passive blowing. Furthermore, we quantitatively assess the friction drag reduction effect based on the streamwise mean velocity profiles. Friction velocity at each measurement location is determined by fitting the slopes of a theoretical wall law taking into account the effect of pressure gradient and the experimental profile in the log-law region so that the effect of roughness is also considered (Fig. 4). As shown in Fig. 5, friction drag reduction effect of 4% - 23% is confirmed through this quantitative assessment.

Key words

Passive control, Drag reduction, Uniform blowing, Airfoil, Wind-tunnel experiment, Roughness

Figures

Fig. 1: Schematic of passive blowing.

Fig. 2: Clark-Y airfoil model.

Fig. 3: Mean velocity profiles at x / c = 0.70:
(a) α = 0°, Rec = 1.55 × 10⁶; (b) α = 6°, Rec = 1.55 × 10⁶.

Fig. 4: Non-dimensionalized mean velocity profiles at x / c = 0.70:
(a) α = 0°, Re_c= 1.55 × 10⁶; (b) α = 6°, Re_c= 1.55×10⁶.

Fig. 5: Local friction drag reduction rate R.