Icing-Tunnel Tests of a Glycol-Exuding, Porous Leading-Edge Ice Protection System

Kohlman, D. L.; Schweikhard, W. G.; Evanich, P.

doi:10.2514/3.57445

Cited by 9 publications

(3 citation statements)

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“…Moreover, researches on the aerodynamic effect of de/anti-icing fluid can be found in the references of [2][3][4][5][6]. Kohlman et al [7] tested a glycol-exuding, porous leading-edge ice protection system. Results indicated that this method is very effective means of preventing ice accretion or removing ice from wings.…”

Section: Introductionmentioning

confidence: 99%

Experimental study of air injection effect on to the surface for preventing ice formation

2020

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In order to prevent the ice-accretion on the airfoil surface, an experimental study was conducted to investigate effect of injecting surrounding air from the surface into the main flow. For this purpose, holes were created at the leading edge of the airfoil. Five parameters of diameter, pitch, angle of position, holes arrangement, and velocity of the outlet flow from the holes were sought. Using principles of experimental design by two-level fractional factorial method, required tests were designed and determined. Conducting tests, the results indicated the injection method significantly reduces weight of ice accreted on the surface. The highest amount of ice mass reduction in experiments reached 85% of the ice mass accreted on the simple airfoil. The diameter and pitch of holes had greatest effect on reducing the mass of ice accreted on the surface, followed by the injection airflow rate and the angle of alignment. Therefore, the injection of air at lower temperature than freezing point is as effective for ice accretion and saves energy rather than using hot-air injection. Moreover, the injected air from holes created a protective layer around the surface, which enhanced the process.

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Section: Introductionmentioning

confidence: 99%

Experimental study of air injection effect on to the surface for preventing ice formation

2020

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“…Suggesting four mechanisms, use of freezing point depressants where the ethylene glycol is expelled during flight through the leading edge slots, surface deformation using pneumatic boots, thermal melting using electrothermal heaters situated on the aircraft's wings, and passing of hot air under the skin of the aircraft (Piccolo tube), and slot injection of hot gas on to the wing surface. Kohlman et al [2] tested a glycol exuding at porous leading-edge ice protection system. Results indicated very effective for preventing ice accretion or removing ice from wings with no significant drag penalty.…”

Section: Introductionmentioning

confidence: 99%

Simulation of different shapes and arrangements of holes over the leading edge of airfoil by blowing to prevent ice accretion

Barzanouni

Gorji-Bandpy

Tabrizi

2020

J Braz. Soc. Mech. Sci. Eng.

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Effect of blowing out on NACA0012 airfoil surface in order to prevent of ice accretion was studied numerically. Holes with regular pattern were generated over the leading edge of airfoil. Velocity of air injection, diameter, pitch of holes, and symmetrical angle of two rows about of cord line and arrangement of holes, diamond, and rectangle were varied. Shear-stress transport k-ω model was chosen to simulate the turbulence closure model, which makes better prediction for the case of pressure gradient over airfoils. Protective layer of air injections caused to prevent water droplets from the impact and strike to the airfoil surface. Results indicated that the diameter has the most effect on lowering of the ice accretion. In addition, pitch of the holes has the second most important role for reduction of ice weight. Reduction of 89% in the ice accretion in the presence of blowing out was achieved.

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“…Kohlman and Albright 10 presented an analytical method of predicting fluid flow rate required of the fluidic ice protection system. This method was developed after the fluidic anti-icing system evaluation in the NASA Lewis icing research tunnel in 1982 11 for which the results were compared with experimental results.…”

Section: Introductionmentioning

confidence: 99%

Computational fluid dynamics investigation of finding appropriate location of fluidic anti-icing protective panel on leading edge of wing

Afghari

Vaziry

Mostofizadeh

2017

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this article, determination of protective panel limits of fluidic anti-icing system on leading edge of the high aspect ratio wing of a piston powered aircraft is studied numerically. Define surfaces of wing to be protected against ice accretion is the most important part of fluidic anti-icing system design. The first step of numerical code is devoted to flow field computation using control volume method. The second step is calculation of droplet’s trajectory and impingement characteristics using the Euler approach and, finally, ice shape and ice accretion rate are obtained using the messenger model. The code was used to obtain ice shape and droplets impingement limit in different sections of the wing and, as a result, protection panel geometry limits were determined, on the wing’s upper and lower surfaces. Also, by the introduced method in this work, ice formation is predicted on NACA0012 airfoil, and a good agreement was shown between predicted ice shape and experimental data. Finally, environmental and airflow parameters effect on the limitation of protective panel are obtained. The results indicated that only two parameters, liquid water content and exposure time have no effect on the panel limits.

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Icing-Tunnel Tests of a Glycol-Exuding, Porous Leading-Edge Ice Protection System

Cited by 9 publications

References 0 publications

Experimental study of air injection effect on to the surface for preventing ice formation

Experimental study of air injection effect on to the surface for preventing ice formation

Simulation of different shapes and arrangements of holes over the leading edge of airfoil by blowing to prevent ice accretion

Computational fluid dynamics investigation of finding appropriate location of fluidic anti-icing protective panel on leading edge of wing

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