Computing aerodynamic characteristics of passenger aircraft of maximum takeoff weight from 6600 to 21000 kg AT cruising, takeoff and landing configuration

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2022-3-7-16

Аuthors

Vlasov A. V.

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

e-mail: avvlasov@ciam.ru

Abstract

Resource-intensive CFD methods, requiring both significant time and computing costs, are usually being employed to compute the aircraft aerodynamic characteristics. Thus, it is reasonable to apply fast semi- empirical methods for the aircraft conceptual design.

The article considers the existing semi-empirical methods for calculating the aircraft aerodynamic characteristics, and compares these methods with each other and verifies them with experimental data. Special focus is given to techniques that allow estimating the flaps and slats effect on the aircraft aerodynamic characteristics. Thus, the Arep’yev and Raymer methods are the two basic methods for the cruising aerodynamic characteristics estimation being considered in this article. To verify the mathematical models, computations of the cruising aerodynamic characteristics of the three aircraft with a maximum takeoff weight from 6600 to 21000 kg were performed by the Arep’ev and Raymer methods, and their results were compared with the experimental data. The high efficiency of the modified Arep’ev method for calculating the aircraft coefficients of lift and drag up to the angles of attack of 12° is demonstrated.

Among the techniques for the takeoff and landing aerodynamic characteristics estimation, the two methods that yield the most correct result were selected as well. Additionally, the article suggests a simple dependence of the additional drag coefficient caused by flaps deflection depending on the angle of their deflection. Comparison of the takeoff and landing aerodynamic characteristics computing results of the three aircraft with maximum takeoff weight from 6600 to 21000 kg with the experimental data was performed as well. This comparison demonstrated the high efficiency of the methods under consideration.

Keywords:

aerodynamic characteristics computing, aircraft lifting force coefficient, aircraft resistance coefficient, flaps impact of aerodynamic characteristics

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