[{“box”:0,”content”:”[if 992 equals=”Open Access”]
Open Access
n
[/if 992]n
n
n
n
n
- n t
n
Siddalingappa P. Kodigaddi, Mohammed Ayaan Khazi, Mounika C.S., Deva N., Sangeetha Patil P., Yathish R., Somashekar V.
[/foreach]
n
n
n[if 2099 not_equal=”Yes”]n
- [foreach 286] [if 1175 not_equal=””]n t
- , , ,
n[/if 1175][/foreach]
[/if 2099][if 2099 equals=”Yes”][/if 2099]nn
Abstract
nIn this research the steady state analysis of a supercritical airfoil is done to understand the flow physics at transonic Mach number regime for various thickness. The modeling of NASA SC (2) 0714 supercritical airfoil with various thickness values is done. The steady state analysis is carried out for different test cases in combination with different thickness, angle of attack and Mach number at 10 km altitude using density-based Reynolds Averaged Navier Stokes solver and k-omega Shear Stress Transport Model. The variation of pressure and velocity is studied with different Mach numbers and given angle of attack. The pressure and velocity counters clearly indicate the formation of shockwave and its location. The results show that the occurrence of shock wave and its location on the surface of the airfoil. The strength of the shockwave formed is affected based on the thickness of the airfoil, the freestream Mach number and the angle of attack. The strength of the shockwave has decreased with decrease in the thickness of the airfoil at given angle of attack and Mach number. Also, the location of the shockwave has
n
Keywords: Aerodynamics, Supercritical airfoil, transonic Mach, SST Model, RANS, CFD
n[if 424 equals=”Regular Issue”][This article belongs to Journal of Polymer and Composites(jopc)]
n
n
n
n
n
n
n[if 992 equals=”Open Access”] Full Text PDF Download[else] nvar fieldValue = “[user_role]”;nif (fieldValue == ‘indexingbodies’) {n document.write(‘Full Text PDF‘);n }nelse if (fieldValue == ‘administrator’) { document.write(‘Full Text PDF‘); }nelse if (fieldValue == ‘jopc’) { document.write(‘Full Text PDF‘); }n else { document.write(‘ ‘); }n [/if 992] [if 379 not_equal=””]n
Browse Figures
n
n[/if 379]n
References
n[if 1104 equals=””]n
- X. Xin, L. Dawei, C. Dehua, W. Zhi and W. Yuanjing, “Supercritical Airfoil Data Corrected for Sidewall Boundary-Layer Effects in Transonic Wind Tunnel,” 2013 Fourth International Conference on Digital Manufacturing & Automation, Shinan, China 2013, pp. 1357-1360, doi: 10.1109/ICDMA.2013.324.
- Experimental Study of Shock Wave Oscillation on SC(2)- 0714 Airfoil Zijie Zhao Xudong Ren, Chao Gao North western Poly technical University (NPU), Xi’an 710072, China Juntao Xiong, Feng Liu, and Shijun Luo University of California, Irvine (UCI), CA 92697-3975
- NASA SC(2)-07 14 Airfoil Data Corrected for Sidewall Boundary-Layer Effects in the Langley 0.3-Meter Transonic Cryogenic Tunnel Renaldo V. Jenkins Langley Research Centre Hampton, Virginia
- Aerodynamic analysis of supercritical NACA sc (2)-0714 airfoil using CFD Ravi Kumar T, Dr. S B Prakash, Department of Thermal Power engineering VTU PG Centre, Mysore-29 VTU Belgaum, Karnataka, India
- Numerical study of a supercritical airfoil/wing with variable-camber technology Wei NIU, Yufei ZHANG, Haixin CHEN, Miao ZHANG School of Aerospace Engineering, Tsinghua University, Beijing 100084, China Shanghai Aircraft Design and Research Institute, Shanghai 201210, China
- Pressure distribution feature-oriented sampling for statistical analysis of supercritical airfoil aerodynamics Runze LI, Yufei ZHANG, Haixin CHEN School of Aerospace Engineering, Tsinghua University, Beijing 100084, China
- Numerical Study of Spike on Blunt Nose Configuration at Supersonic Speed Sajida Malik, Zeeshan Ahmed, Sher Afzal, Usman Aslam CESAT, Islamabad, Pakistan.
- Sobieczky, Helmut & Geißler, W. & Hannemann, M (2007). Numerical tools for unsteady viscous flow control.10.1007/BFb0107118.
- Zhang, Yufei & Chen, Haixin & Miao, Zhang & Meihong, Zhang & Tiejun, Liu & Fu, Song. (2011) Supercritical Wing Design and Optimization for Transonic Civil Airplane. 10.2514/6.2011-27.
- Computer-Aided Analysis of Interferometric Images of Unsteady Aerodynamic Flows MC Wilder MCAT lnc., San Jose, CAM S Chandrasekhara
- Han, Zhong-Hua & Deng, J. & Liu, Jun & Zhang, ke-shi & Song, Wenping. (2012) Design of laminar supercritical airfoils based on Navier-Stokes equations. 1. 706-715.
- Numerical Investigation on the Reynolds Number Effects of Supercritical Airfoil Dawei Liua, Yuanjing Wanga, Dehua Chena, Xin Penga, Xing Xua State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, PRC b China Aerodynamic Research and Development Center, High Speed Aerodynamics Institute, Mianyang, 622661, PRC
- Computational Analysis on Porosity Effect on Aerodynamic Characteristic of Supercritical Airfoil Shan Jixiang, Zhou Ling, Peng Xin, Zhong Shidong High Speed Aerodynamic Institute, China Aerodynamics Research & Development Center, Mianyang, China [email protected]
- RANS computation of transonic buffet over a supercritical airfoil A.B.M. Toufique Hasana *, Md. Mahbub Alamba Assistant Professor, Department of Mechanical Engineering, Bangladesh University of Engineering and Technology (BUET), Dhaka-1000, Bangladesh b Engineer Officer, Biman Bangladesh Airlines Limited, Dhaka, Bangladesh
- Virtual boundary method for inviscid transonic flow over supercritical airfoils J. Solarte-Pineda, P.C. Greco Jr. Department of Aeronautical Engineering, School of Engineering of Sao Carlos, University of Sao Paulo, Brazil
- Study of boundary layer transition on supercritical natural laminar flow wing at high Reynolds number through wind tunnel experiment, Jiakuan Xu, Ziyuan Fu, Junqiang Bai, Yang Zhang, Zhuoyi Duan, Yanjun Zhang
- High fidelity gust simulations over a supercritical airfoil B. Tartinville, NUMECA International S.A., 189 Chaussée de la Hulpe, 1170 Brussels, Belgium. V. Barbieux NUMFLO, Boulevard Initialis, 7000 Mons, Belgium and, L. Temmerman NUMECA International S.A., 189 Chaussée de la Hulpe, 1170 Brussels, Belgium
- Aerodynamic Shape Optimization of an Adaptive Morphing Trailing Edge Wing Zhoujie Lyu Joaquim R. R. Martins Department of Aerospace Engineering, University of Michigan, Ann Arbor, MI
nn[/if 1104][if 1104 not_equal=””]n
- [foreach 1102]n t
- [if 1106 equals=””], [/if 1106][if 1106 not_equal=””],[/if 1106]
n[/foreach]
n[/if 1104]
nn
nn[if 1114 equals=”Yes”]n
n[/if 1114]
n
n
n
| Volume | 11 |
| [if 424 equals=”Regular Issue”]Issue[/if 424][if 424 equals=”Special Issue”]Special Issue[/if 424] [if 424 equals=”Conference”][/if 424] | 13 |
| Received | October 30, 2023 |
| Accepted | November 30, 2023 |
| Published | March 29, 2024 |
n
n
n
n
n
nn function myFunction2() {n var x = document.getElementById(“browsefigure”);n if (x.style.display === “block”) {n x.style.display = “none”;n }n else { x.style.display = “Block”; }n }n document.querySelector(“.prevBtn”).addEventListener(“click”, () => {n changeSlides(-1);n });n document.querySelector(“.nextBtn”).addEventListener(“click”, () => {n changeSlides(1);n });n var slideIndex = 1;n showSlides(slideIndex);n function changeSlides(n) {n showSlides((slideIndex += n));n }n function currentSlide(n) {n showSlides((slideIndex = n));n }n function showSlides(n) {n var i;n var slides = document.getElementsByClassName(“Slide”);n var dots = document.getElementsByClassName(“Navdot”);n if (n > slides.length) { slideIndex = 1; }n if (n (item.style.display = “none”));n Array.from(dots).forEach(n item => (item.className = item.className.replace(” selected”, “”))n );n slides[slideIndex – 1].style.display = “block”;n dots[slideIndex – 1].className += ” selected”;n }n”}]