The Effect of the Repair Patch on the Aerodynamic Characteristics of a Wing with the Leading Edge Icing

Aeronautical and Space-Rocket Engineering


Аuthors

Smirnov A. V.1*, Korchagina M. V.2**, Stepanov V. N.2, 3***

1. Federal Unitary Enterprise State Scientific Research Institute of Civil Aviation, Moscow, Russia
2. Don State Technical University, DSTU, 1, Gagarin square, Rostov-on-Don, 344003, Russia
3. RZGA No. 412 JSC, Rostov-on-Don, Russian Federation

*e-mail: smirnov_av@gosniiga.ru
**e-mail: ms.korchaginamv@mail.ru
***e-mail: st_fem@bk.ru

Abstract

Wing icing during descent and landing has always been an extreme situation in flight, especially for passenger aircraft. The unpredictable behavior of the aircraft lifting surface due to changes in the wing profile caused by ice buildup at minimum landing speeds depends solely on the human factor, namely pilot skill and experience. This study evaluates the impact of the repair patch on a medium-range aircraft wing panels in airflow with leading-edge icing. Lifetime studies and remedial repairs are among the conditions for maintaining airworthiness. Loss of load-bearing capacity of aircraft wing panels due to corrosion damage or panel cracks is compensated for by installing repair patches externally. Internal installation of compensation elements is less common, as internal installation alters the wing's structural composition. The wing lifetime modifications are being accomplished by installing external patches, partially altering the flow-around pattern of the wing and its performance. The objective of this study consists in studying the impact of the wing icing with a repair patch on the aircraft aerodynamic performance during descent and landing.
This study examines the aerodynamic characteristics of an isolated wing while descent and landing for various angles of attack for a clean wing, a wing with a repair patch on the upper panel, and a wing with icing.
The article presents the studies of the flow velocities over the wing with leading edge icing at two modes, namely descent (with the wing high-lift devices retracted) and landing (with the flaps extended to 38°) for various angles of attack. To compare the adequacy of the results in each mode, flow simulations were performed for a clean wing (without the patch), a wing with a repair patch in the front spar area, a clean wing with leading edge icing, and a wing with a repair patch and leading edge icing. Generalized wing polars, quality curves, and changes in the of the center of pressure position relative to the bсах were plotted for the two modes and seven and four wing angles of attack.
The obtained simulation results allow evaluating the repair patch impact on the of a wing with icing performance (Сy = f(Cx), K = f(a), Xс.d. = f(α)) in the flow under the most unfavorable operating conditions. The methods and results of this study may be applied for a preliminary analysis of the aerodynamic characteristics of an aircraft with repair patches for various operating conditions. This study continuation may be the study of the of ice formation nature directly on the repair patch under various conditions and identification of its effect on the aerodynamic characteristics. A study of a wing aerodynamics with multiple patches under icing conditions is possible as well.

Keywords:

wing with icing of the leading edge in the flow, wing with icing of the leading edge and repair patch in the flow, wing with icing of the leading edge and repair patch at landing and pre-landing angles of attack with retracted and extended mechanization

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