Which books should I study to understand more about Supercritical airfoils?
Introduction to Transonic Aerodynamics

Roelof Vos, Saeed Farokhi (more)  

  


  Written to teach students the nature of transonic flow and its
  mathematical foundation, this book offers a much-needed introduction
  to transonic aerodynamics. The authors present a quantitative and
  qualitative assessment of subsonic, supersonic and transonic flow
  around bodies in two and three dimensions. The book reviews the
  governing equations and explores their applications and limitations as
  employed in modeling and computational fluid dynamics.




Transonic Aerodynamics of Airfoils and Wings

W.H. Mason (more)  

  


  Professor emeritus by the Virginia Tech, expert in aerospace
  engineering who worked at Grumman Aerospace where he served in the
  structural mechanics section and later in aerodynamics and worked on a
  number of high-profile projects, including the Grumman X-29. Has
  taught classes — including his "famous" Configuration Aerodynamics
  course.




Review of NASA Supercritical Airfoils

Richard T. Whitcomb (more)  

  


  NASA supercritical airfoils are characterized by a substantially
  reduced curvature of the midcord region of the upper surface together
  with increased camber near the trailing edge. The basic aerodynamic
  phenomena associated with the airfoils and representative wind tunnel
  results are discussed. The results indicate that the drag rise Mach
  numbers for NASA supercritical airfoils are 0.1 higher than for
  comparable NACA 6-series airfoils. A recent analytic method for
  predicting the aerodynamic characteristics of supercritical airfoils
  is described. The flight demonstration programs of three applications
  of supercritical airfoils utilizing the F-8, T-2C and F-111 as test
  beds are summarized.


Richard T. Whitcomb on Wikipedia.



NASA Supercritical Airfoils, A Matrix of Family-Related Airfoils

Charles D. Harris (more)  

  


  The NASA supercritical airfoil development program is summarized in a
  chronological fashion. Some of the airfoil design guidelines are
  discussed, and coordinates of a matrix of family related supercritical
  airfoils ranging from thicknesses of 2 to 18 percent and over a design
  lift coefficient range from 0 to 1.0 are presented.




Supercritical Airfoil Design for Future HALE Concepts

Kasim Biber, Carl P. Tilmann (more)  

  


  This paper presents design and analysis of a new airfoil for future
  High-Altitude Long-Endurance (HALE) aircraft that has an operational
  condition at supercritical speeds. The XFOIL and MSES computational
  codes were used to design, modify and analyze the airfoil.




Design of Laminar Supercritical Airfoils Based on Navier-Stokes Equations

Zhong-Hua HAN, Jie DENG, Jun LIU,  Ke-Shi, ZHANG, Wen-Ping SONG (more)  

  


  This paper aims to develop a suit of design methods and
  tools for laminar supercritical airfoils, based on 
  high-fidelity computational fluid dynamics (CFD). The reliable 
  transition perdition method, efficient inverse design and 
  global optimization design methods are regarded as 
  three key issues, which are addressed in this paper. The automatic 
  transition prediction method coupling Navier-Stokes equations 
  flow solver and eN linear 
  stability analysis method is applied to the design and analysis of the
  laminar supercritical airfoils; inverse design and optimization design
  methods based on kriging surrogate model is developed to 
  attain favorable pressure gradient while reducing wave 
  drag; efficient optimization based on kriging model and an 
  improved EI (expected improvement) method is developed for finding 
  the global optimum.




NASA Technical Memorandum 103933 An Experimental Investigation of a Supercritical Airfoil at Transonic Speeds

George G. Mateer, H. Lee Seegmiller, Lawrence A. Hand and Joachim Szodruch (more)  

  


  Benchmark experimental data obtained in the two-dimensional, transonic
  flow field surrounding a supercritical airfoil are presented. Airfoil
  surface and tunnel wall pressure and LDV measurements are used to
  describe the flow on the model, above the wing and in the wake.
  Comparisons are made with calculations using the Reynolds-averaged
  Navier-Stokes equations. The results illustrate the performance of two
  turbulence models in both separated and attached flows. The largest
  differences between theory and experiment occurred in separated flows
  with the Johnson and King turbulence model providing the best
  estimates.




Analysis of Aerodynamic Characteristics of a Supercritical Airfoil for Low Speed Aircraft

P.Sethunathan, M.Niventhran, V.Siva, R.Sadhan Kumar (more)  

  


  The main goal of the proposed paper is the analysis of aerodynamic
  characteristics of an various supercritical airfoils like 0406, 0412,
  0706 and 1006 influence on the  dramatic improvement in lift and
  reduction of drag in low speed aircraft. In a precedent work,  a  cusp 
  like  structure  at  the  trailing  edge  of  an  unsymmetrical 
  airfoil  produces a  very  high  improvement  in  climbing performance
  of an aircraft.




Two-dimensional Wind-tunnel Tests of a NASA Supercritical Airfoil with Various High-lift Systems

E. Omar et Al. (more)  

  


  Three high lift systems for a 9.3 percent blunt based, supercritical
  airfoil were designed, fabricated, and wind tunnel tested. A method
  for calculating the viscous flow about two dimensional multicomponent
  airfoils was evaluated by comparing its predictions with test data. A
  comparison of high lift systems derived from supercritical airfoils
  with high lift systems derived from conventional airfoils is
  presented. The high lift systems for the supercritical airfoil were
  designed to achieve maximum lift and consisted of: (1) a single
  slotted flap, (2) a double slotted flap and a leading edge slat, and
  (3) a triple slotted flap and a leading edge slat.




Aerodynamic Characteristics of an 11-percent-thick Symmetrical Supercritical Airfoil at Mach Numbers Between 0.30 and 0.85

Blackwell, J. A., Jr. (more)  

  


  Abstract: The aerodynamic characteristics of an 11 percent thick
  symmetrical supercritical airfoil were determined in an 8 foot
  transonic pressure tunnel over a Mach number range of 0.30 to 0.85.
  The Reynolds number of the tests, based on the airfoil chord, varied
  with Mach number over a range of 360 million to 774 million. The
  geometric angle of attack varied from -0.5 to 10.5 deg. The abrupt
  drag rise for the supercritical airfoil at zero normal force
  conditions occurs at a Mach number just above 0.82. The corresponding
  drag rise Mach number for a conventional NACA 0012 airfoil is
  approximately 0.70. At zero normal force conditions, the level of
  supervelocity over the supercritical airfoil is considerably reduced
  from that for the NACA 0012 airfoil. Also, the shock wave for the
  supercritical airfoil is substantially weaker than that for the NACA
  0012 airfoil.