Numerical Investigation of Aerodynamic Hysteresis for Transonic Flow Over a Supercritical Airfoil

Rahman, Md. Ashikur; Hasan, A. B. M. Toufique; Labib, Md. Itmam

doi:10.1016/j.proeng.2015.05.021

Cited by 1 publication

(6 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…These drag coefficient values appear to undergo small but non-negligible changes with the alteration of the upper camber. The drag coefficient result from the simulation appears to be reasonably validated by Moelyadi's [7] and Rahman's [10] baseline RAE2822 CFD data for AoA < 10 degrees. The lift-to-drag ratio is a reasonable first approximation to examine the overall effect of the upper camber modification on the airfoil performance.…”

Section: Lift and Drag Coefficientsmentioning

confidence: 58%

“…Both surface pressure and boundary layer pitot and static pressure tests were conducted in order to calculate the airfoil pressure coefficient profile for the selected wind speed of Mach 0.729 at the 2.79 degree angle of attack [4]. Rahman, et al [10] obtained RAE 2822 simulations coefficients by numerical simulation including aerodynamic hysteresis at the same Mach number as Cook et al [4] of 0.729. The computational domain around the RAE 2822 airfoil used by Rahman et al [10] utilized the 1-equation Spalart-Allmaras turbulent equation model with an identical ANSYS software and domain shape as Araya's [7] template with a drag coefficient range from -4 to 18 degree angles of attack.…”

Section: Literature Reviewmentioning

confidence: 99%

“…Rahman, et al [10] obtained RAE 2822 simulations coefficients by numerical simulation including aerodynamic hysteresis at the same Mach number as Cook et al [4] of 0.729. The computational domain around the RAE 2822 airfoil used by Rahman et al [10] utilized the 1-equation Spalart-Allmaras turbulent equation model with an identical ANSYS software and domain shape as Araya's [7] template with a drag coefficient range from -4 to 18 degree angles of attack. Therefore, Rahman's [10] paper was an ideal reference for the CFD drag coefficients along with Moelyadi's [7] paper.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The computational domain around the RAE 2822 airfoil used by Rahman et al [10] utilized the 1-equation Spalart-Allmaras turbulent equation model with an identical ANSYS software and domain shape as Araya's [7] template with a drag coefficient range from -4 to 18 degree angles of attack. Therefore, Rahman's [10] paper was an ideal reference for the CFD drag coefficients along with Moelyadi's [7] paper. The prevalence of simulations obtaining both lift coefficients and pressure coefficient distributions made the RAE 2822 an ideal selection for supercritical airfoil performance simulations and allowed an acceptable level of validation for this work.…”

Section: Literature Reviewmentioning

confidence: 99%

“…The RAE 2822 ANSYS Fluent simulation model was validated by Moelyadi's [7] and Rahman's [10] data. These comparisons demonstrated the accuracy of the model for the flow conditions of the referenced material.…”

Section: Accuracy and Grid Dependenciesmentioning

confidence: 99%

See 4 more Smart Citations

Effects of Supercritical Airfoil Upper Camber Modification on Overall Airfoil Performance

Choudhury¹,

Cui²,

Motevalli³

2020

World Congress on Momentum, Heat and Mass Transfer

View full text Add to dashboard Cite

This paper explores the effects of a supercritical airplane wing airfoil modification on the aerodynamic characteristics of the wing using primarily lift and drag characteristics. This research is motivated by new approaches in dynamic wing re-configuration studies initiated by NASA. Wing re-configuration via mechanical wing movement has been successfully implemented in military aircraft. The latest approach examines changes in wing characteristics in a dynamic fashion ("morphing") using smart material and moving parts in the entire wing surface. To better understand airfoil modification effects on the aerodynamics of the process, the super-critical airfoil upper camber is varied. ANSYS/Fluent software is used to develop the numerical simulation for compressible flows in the low transonic regime (Mach number 0.7-0.9). The baseline simulations have been successfully validated with published data and selected experimental results. Simulation results for lift, drag, and pressure coefficients along with the flow Mach numbers for various angles of attack have been produced to evaluate airfoil modifications. The preliminary findings point to an improved airfoil lift characteristics by increasing the airfoil upper camber. As expected, increased drag coefficient appear to counteract the improved lift characteristics.

show abstract

Section: Lift and Drag Coefficientsmentioning

confidence: 58%

Section: Literature Reviewmentioning

confidence: 99%