METHOD FOR PREDICTING AERODYNAMIC PROPERTIES OF A NACA 4412 AIRFOIL

Abstract

ABSTRACT A method (100) for predicting aerodynamic properties of a NACA 4412 airfoil. Further, the method comprising conducting computational fluid dynamics (CFD) analysis on the airfoil while varying its thickness to observe changes in the coefficient of pressure. Further, the method (100) comprising the steps of applying the Prandtl-Glauert rule to estimate compressibility effects in subsonic flow conditions and the Karman-Tsien rule for transonic flow conditions. Further, the method (100) comprising the steps of comparing computational results of the coefficient of pressure with manually calculated results to determine the degree of variation and reliability of the predictions. Further, the method (100) comprising the steps of utilizing the insights gained to provide recommendations for aerodynamic design applications in aerospace engineering. <>

Specification

Description:FIELD OF THE DISCLOSURE
[0001] This invention generally relates to the field of aerospace engineering and, in particular, to a method for predicting aerodynamic properties of airfoils using computational fluid dynamics (CFD) analysis, which incorporates advanced modeling techniques to enhance the accuracy and efficiency of aerodynamic performance assessments in both subsonic and transonic flow regimes.
BACKGROUND
[0002] The subject matter discussed in the background section should not be assumed to be prior art merely as a result of its mention in the background section. Similarly, a problem mentioned in the background section or associated with the subject matter of the background section should not be assumed to have been previously recognized in the prior art. The subject matter in the background section merely represents different approaches, which in and of themselves may also correspond to implementations of the claimed technology.
[0003] The performance of airfoils is critical in the design and oper , Claims:WE CLAIM:
1. A method (100) for predicting aerodynamic properties of a NACA 4412 airfoil, the method comprising the steps of:
conducting computational fluid dynamics (CFD) analysis on the airfoil while varying its thickness to observe changes in the coefficient of pressure;
applying the Prandtl-Glauert rule to estimate compressibility effects in subsonic flow conditions and the Karman-Tsien rule for transonic flow conditions;
comparing computational results of the coefficient of pressure with manually calculated results to determine the degree of variation and reliability of the predictions; and
utilizing the insights gained to provide recommendations for aerodynamic design applications in aerospace engineering.

2. The method (100) as claimed in claim 1, wherein the step of conducting computational fluid dynamics (CFD) analysis further includes the use of specific boundary conditions, including atmospheric pressure and a flow velocity of 50 m/s, to accurately simulate the aerodynamic performance of the airf

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