![]() Prevalently the objective of this examination was to numerically decide whether or not the aerodynamic performance of an airfoil can be improved by presenting a retrogressive confronting step on the upper surface of the airfoil. In particular, the research takes into consideration two types of aircraft, namely cargo aircraft and military high-speed aircraft and compares their airfoil characteristics using their NACA airfoils as well as computational fluid dynamics. Moreover, the numerical result of lift coefficient is compared to the available experimental result in order to validate the carried out numerical simulation. Abstract: This paper exemplifies the influence of the purpose of an aircraft on the aerodynamic properties of its airfoil. airfoil of the slotted shape and a NACA 64A-series airfoil of the same thickness ratio indicated that for a design-section normal-force coefficient of 0. The analyzed results demonstrate the aerodynamic performances in terms of drag and lift coefficients, pressure coefficients, static temperature for the various angle of attacks and mach numbers. Computational examinations were directed to upgrade the aerodynamic performance of the airfoil. For a variation of mach number extending from 0.3 to 0.6, the point of separation was resolved to employ CFD analysis. The numerical simulation was carried out with varying angle of attacks ranging from 0˚ to 15˚. The test program covered a Mach number range of 0.30 to 0.82 and a Reynolds number range of 3.0 to 45. Spalart-Allmaras turbulence model is employed on the ANSYS Fluent environment due to the transonic flow condition. Tests were conducted in the two-dimensional test section of the Langley 0.3-m Transonic Cryogenic Tunnel on a NACA 0012 airfoil to obtain aerodynamic data as a part of the Advanced Technology Airfoil Test (ATAT) program. NACA 4412 Airfoil 4 digit code used to describe airfoil shapes 1st digit - maximum camber in percent chord 2nd digit - location of maximum camber along chord line (from leading edge) in tenths of chord 3rd and 4th digits - maximum thickness in percent chord NACA 4412 with a chord of 6 Max camber: 0. ![]() Aerodynamic characteristics have been investigated for KFm-1, KFm-2, and KFm-3 followed by a comparison with NACA 4412 airfoil. KFm series airfoil family has better stability and low stalling effects which have made its use for low weight carrying flight. There were 40 pressure taps along the upper and lower surfaces of the. In the experiments chosen for comparison, Re c 250 000 and freestream M 0:03265 (U 1 11:1 m/s). Frequently, the question arises as to what airfoil or airfoils were used in the wing design of a particular aircraft. ![]() This article presents the aerodynamic characteristics of Kline-Fogleman modified (KFm) airfoil. The airfoil model had span b 0:610 m and chord length c 0:347 m, and was placed in a wind tunnel with dimensions 0:610 m wide 1:004 m high (see gure 1(b)). David LednicerAeromechanical Solutions LLC15219 NE 71st CourtRedmond, WA.
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