Wind Tunnel Calibration, Corrections and Experimental Validation for Fixed-Wing Micro Air Vehicles Measurements

Aboelezz, Ahmed; Elqudsi, Yunes; Hassanalian, Mostafa; Desoki, Ahmed

doi:10.3846/aviation.2019.11975

Cited by 8 publications

(4 citation statements)

References 22 publications

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“…The estimated values of these correction factors are ϵ sb = 0.004 4, ϵ wb = 0.002 4 and ϵ sc = 0.000 7. The dynamic pressure is corrected by a factor q c / q , which is given by equation (8) 36 where normalϵm is the maximum blockage (normalϵm=normalϵsb+normalϵwb+normalϵsc) estimated from the wind tunnel. The corrected values of force coefficients are given by equation (9) 37 and equation (10) 37 where Cl1 and Cd1 are the measured values of lift and drag coefficients, respectively, from the wind tunnel; Clexp and Cdexp are the corrected values of lift and drag coefficients, respectively, by considering total blockage from the wind tunnel.…”

Section: Methodsmentioning

confidence: 99%

Aerodynamic investigation of Passer domesticus inspired biomimetic wing at low Reynolds number

Shaik

Hazarika

2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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A biomimetic wing is designed by considering the wing of a natural flyer (Passer Domesticus) as a reference. Since the birds have thin wings, Bergey BW-3, a thin and highly cambered airfoil, is used to design wing’s cross-section. To investigate the aerodynamic characteristics of biomimetic wing, numerical and experimental studies are carried out at low Reynolds number (Re) ranging from 2.5x10^4 to 1x10^5. The performance of biomimetic wing is compared with rectangular and elliptical wings at Re = 5x10^4. It is observed that the separation bubble formed over the surface of biomimetic wing at Re = 2.5x10^4 is not strong enough to influence the lift coefficient but dramatically increases the drag coefficient when the mean angle of attack exceeds 18^0. It is observed that the drop in lift coefficient of rectangular wing is higher than that of other wings due to presence of sharp edges in the planform. The lowest drag coefficient is witnessed in elliptical wing but it also has lowest lift coefficient due to the interaction between the separation bubble and tip vortices. But the biomimetic wing offers highest lift coefficient with a considerable amount of drag. It is observed that the flow separates dramatically as the mean angle of attack increases beyond the stall angle in rectangular and elliptical wings. But a delay in the flow separation is observed in case of biomimetic wing after the stall angle. It is also observed that the suction over the wing surface of biomimetic wing is more at wingroot than that at wingtip, which may provide good stability during flight conditions. The enhanced aerodynamic performance of the biomimetic wing is due to change in shape of the wing along the span which has a strong influence over its effective angle of attack with respect to the incoming flow.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic investigation of Passer domesticus inspired biomimetic wing at low Reynolds number

Shaik

Hazarika

2022

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…Because certain aeronautic situations require aircraft to go through extremes of speed and temperature, balances are designed to assist in the design and testing process of these aircraft. Certain balances were designed to handle supersonic [9] and hypersonic flow [10], [11], [12], as well as able to read forces in areas where the Reynold's number is significantly lower than normal conditions [13], [14]. Extreme cold temperatures are also considered when designing aircraft to fly high in the atmosphere, so a normal force balance must be calibrated correctly to negate the thermal compression the balance experiences [15].…”

Section: List Of Figuresmentioning

confidence: 99%

Design optimization of a wind tunnel force balance using stepwise response surface method

Chaisson

Lee²,

Burns³

2022

J Mech Sci Technol

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applied to a body during a wind tunnel test. The balance is equipped with strain gauges that measure structural deformations for evaluation of the forces and moments being applied to the body. The force balance is required to have structural safety under a large roll moment, due to design changes with the testing apparatus. The balance must be optimized to allow for this increased roll moment while guaranteeing the balance will not fail and the gauges within the balance will generate an acceptable gauge reading.

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“…[1][2][3] To improve the data accuracy of the wind tunnel test, the development of new support system is one of the urgent problems to be solved. Significant efforts, such as data correction procedures 4,5 and magnetic suspension and balance system (MSBS), 6 are developed to minimize or eliminate the shortcomings of model mounts. A wire-driven parallel robot (WDPR) suspension system is a type of parallel robots, the obvious advantage of which is the avoidance of the above drawback when it is used as a model suspension system in a wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

Wire-driven parallel robot suspension system for SDM in a low-speed wind tunnel

Peng

Lin

et al. 2023

Advances in Mechanical Engineering

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A wire-driven parallel robot with eight wires (WDPR-8) acting as the suspension system for an aircraft model in a low-speed wind tunnel is introduced in this paper. A kinematics model for WDPR-8 is established here. A theoretical basis is also provided, through which movement control of the model is achieved by changing the wire length. A model motion control subsystem, a monocular vision measurement subsystem for the model position, and a data acquisition subsystem were also developed for WDPR-8. A prototype of WDPR-8 was built and mounted in a low-speed wind tunnel with an open test section. A six-component strain-gauge balance was installed inside the test model to acquire aerodynamic parameters. The aerodynamic coefficients of the static test show reasonable agreement with reference results. The difference between the test result of WDPR-8 and the results from reference is smaller in the positive angle of attack than the negative angle of attack, and the total difference between WDPR-8 and other facilities is under 10%. Pitch dynamic tests with different amplitudes and frequencies were used to verify the aerodynamic hysteresis phenomena. The research indicates it is successful that the solution of measuring aerodynamic parameters with strain-gauge balance set into the standard dynamic model suspended by WDPR. It demonstrates that WDPR-8 is effective and feasible as a model suspension system in a low-speed wind tunnel. Furthermore, test results without interference correction in accordance with the reference data proves that the interference of Wire-Driven support system to flow field during wind tunnel tests is negligible. Finally, WDPR suspension system introduced in this paper will remarkably improve the efficiency and accuracy in wind tunnel test.

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Wind Tunnel Calibration, Corrections and Experimental Validation for Fixed-Wing Micro Air Vehicles Measurements

Cited by 8 publications

References 22 publications

Aerodynamic investigation of Passer domesticus inspired biomimetic wing at low Reynolds number

Aerodynamic investigation of Passer domesticus inspired biomimetic wing at low Reynolds number

Design optimization of a wind tunnel force balance using stepwise response surface method

Wire-driven parallel robot suspension system for SDM in a low-speed wind tunnel

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