EXPERIMENTAL INVESTIGATION ON AERODYNAMIC COEFFICIENTS OF A FLYING WING AIRCRAFT WITH DIFFERENT LEADING EDGE SWEEP ANGLES

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DEHGHAN MANSHADI MOJTABA; EILBEIGI MEHDI; BAZAZ ZADEH MEHRDAD; VAZIRY MOHAMMAD ALI

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Journal: Modares Mechanical Engineering Year:2016 | Volume:16 | Issue:5 Page(s): 303-311

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Title

EXPERIMENTAL INVESTIGATION ON AERODYNAMIC COEFFICIENTS OF A FLYING WING AIRCRAFT WITH DIFFERENT LEADING EDGE SWEEP ANGLES

Author(s)

DEHGHAN MANSHADI MOJTABA | EILBEIGI MEHDI | BAZAZ ZADEH MEHRDAD | VAZIRY MOHAMMAD ALI | Issue Writer Certificate

Keywords

FLYING WINGQ1

LAMBDA WINGQ1

AERODYNAMIC COEFFICIENTSQ2

SWEEP ANGLEQ1

Abstract

The AERODYNAMIC COEFFICIENTS characteristics over a lambda-shaped FLYING WING aircraft with 55o-30o leading edge SWEEP ANGLEs have been investigated in a closed circuit low speed wind tunnel. The experiments were conducted at tunnel velocity of 90 m/s, the angles of attack of -6 to 17 and the sideslip angles of -8 to 8 degrees. All forces and moments were measured using an external six-component force balance located below the wind tunnel. The wall corrections were also performed for all test conditions. To improve the aircraft longitudinal stability characteristics, a new model with an increased leading edge SWEEP ANGLE of 2 degrees was also tested and compared with the original model. A “pitchup” phenomenon determined to occur at a rather low angle of attack of a=7.7 degrees, although it occurred at the higher angle of attack of a=8.7 degrees for the increased SWEEP ANGLE model which means an increase in useable lift of the aircraft. Moreover, off-surface pressure measurement over the wing surface was conducted to examine the onset and development of the flow separation over the wing surface. The results showed that the flow separation started at the trailing edge crank location and extended to the other parts of the wing, especially the outer wing.

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APA: Copy

DEHGHAN MANSHADI, MOJTABA, EILBEIGI, MEHDI, BAZAZ ZADEH, MEHRDAD, & VAZIRY, MOHAMMAD ALI. (2016). EXPERIMENTAL INVESTIGATION ON AERODYNAMIC COEFFICIENTS OF A FLYING WING AIRCRAFT WITH DIFFERENT LEADING EDGE SWEEP ANGLES. MODARES MECHANICAL ENGINEERING, 16(5), 303-311. SID. https://sid.ir/paper/177927/en

Vancouver: Copy

DEHGHAN MANSHADI MOJTABA, EILBEIGI MEHDI, BAZAZ ZADEH MEHRDAD, VAZIRY MOHAMMAD ALI. EXPERIMENTAL INVESTIGATION ON AERODYNAMIC COEFFICIENTS OF A FLYING WING AIRCRAFT WITH DIFFERENT LEADING EDGE SWEEP ANGLES. MODARES MECHANICAL ENGINEERING[Internet]. 2016;16(5):303-311. Available from: https://sid.ir/paper/177927/en

IEEE: Copy

MOJTABA DEHGHAN MANSHADI, MEHDI EILBEIGI, MEHRDAD BAZAZ ZADEH, and MOHAMMAD ALI VAZIRY, “EXPERIMENTAL INVESTIGATION ON AERODYNAMIC COEFFICIENTS OF A FLYING WING AIRCRAFT WITH DIFFERENT LEADING EDGE SWEEP ANGLES,” MODARES MECHANICAL ENGINEERING, vol. 16, no. 5, pp. 303–311, 2016, [Online]. Available: https://sid.ir/paper/177927/en

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