A Sample of NASA Langley Unsteady Pressure Experiments for Computational Aerodynamics Code Evaluation

As computational fluid dynamics methods mature, code development is rapidly transitioning from prediction of steady flowfields to unsteady flows. This change in emphasis offers a number of new challenges to the research community, not the least of which is obtaining detailed, accurate unsteady experimental data with which to evaluate new methods. Researchers at NASA Langley Research Center (LaRC) have been actively measuring unsteady pressure distributions for nearly 40 years. Over the last 20 years, these measurements have focused on developing high-quality datasets for use in code evaluation. This paper provides a sample of unsteady pressure measurements obtained by LaRC and available for government, university, and industry researchers to evaluate new and existing unsteady aerodynamic analysis methods. A number of cases are highlighted and discussed with attention focused on the unique character of the individual datasets and their perceived usefulness for code evaluation. Ongoing LaRC research in this area is also presented.

[1]  Kumar Bhatia,et al.  AEROELASTIC CHALLENGES FOR A HIGH SPEED CIVIL TRANSPORT , 1993 .

[2]  Robert M. Bennett,et al.  NACA 0012 benchmark model experimental flutter results with unsteady pressure distributions , 1992 .

[3]  Robert C. Scott,et al.  The Benchmark Active Controls Technology model aerodynamic data , 1997 .

[4]  Peter Hartwich,et al.  Method for perturbing multiblock patched grids in aeroelastic and design optimization applications , 1997 .

[5]  Robert M. Bennett,et al.  Experimental unsteady pressures at flutter on the Supercritical Wing Benchmark Model , 1993 .

[6]  M. Gibbons,et al.  Aeroelastic Calculations Using CFD for a Typical Business Jet Model , 1996 .

[7]  Maynard C. Sandford,et al.  Measured unsteady transonic aerodynamic characteristics of an elastic supercritical wing , 1987 .

[8]  É. Robert,et al.  Flow and Turbulence Modeling and Computation of Shock Buffet Onset for Conventional and Supercritical Airfoils , 1998 .

[9]  Russ D. Rausch,et al.  Transonic Dynamics Tunnel Force and Pressure Data Acquired on the HSR Rigid Semispan Model , 1999 .

[10]  R Waszak Martin,et al.  Modeling the Benchmark Active Control Technology Wind-Tunnel Model for Application to Flutter Suppression , 1996 .

[11]  W. M. Adams,et al.  A Digital Program for Calculating the Interaction Between Flexible Structures, Unsteady Aerodynamics and Active Controls , 1979 .

[12]  C. V. Eckstrom,et al.  Drones for aerodynamic and structural testing /DAST/ - A status report , 1978 .

[13]  É. Robert,et al.  Cryogenic Tunnel Pressure Measurements on a Supercritical Airfoil for Several Shock Buffet Conditions , 1997 .

[14]  Martin R. Waszak,et al.  BACT Simulation User Guide (Version 7.0) , 1997 .

[15]  Pierce L. Lawing,et al.  Transonic unsteady pressure measurements on a supercritical airfoil at high Reynolds numbers , 1989 .

[16]  David M. Schuster,et al.  An Overview of Unsteady Pressure Measurements in the Transonic Dynamics Tunnel , 2000 .

[17]  Maynard C. Sandford,et al.  Unsteady-Pressure and Dynamic-Deflection Measurements on an Aeroelastic Supercritical Wing , 1991 .

[18]  Maynard C. Sandford,et al.  Transonic region of high dynamic response encountered on an elastic supercritical wing , 1989 .

[19]  R. H. Ricketts,et al.  Geometric and structural properties of a rectangular supercritical wing oscillated in pitch for measurement of unsteady transonic pressure distributions , 1983 .

[20]  W. K. Anderson,et al.  Navier-Stokes Computations of Vortical Flows Over Low-Aspect-Ratio Wings , 1987 .

[21]  Robert M. Bennett,et al.  The benchmark aeroelastic models program: Description and highlights of initial results , 1992 .

[22]  M. G. Farmer.  A two-degree-of-freedom flutter mount system with low damping for testing rigid wings at different angles of attack , 1982 .

[23]  Maynard C. Sandford,et al.  Steady pressure measurements on an Aeroelastic Research Wing (ARW-2) , 1994 .

[24]  Michael H. Durham,et al.  Pressure measurements on a rectangular wing with a NACA0012 airfoil during conventional flutter , 1992 .

[25]  R. Bartels,et al.  Computation of shock buffet onset for a conventional and supercritical airfoil , 1997 .

[26]  F. W. Cazier,et al.  Static and unsteady pressure measurements on a 50 degree clipped delta wing at M = 0.9. [conducted in the Langley Transonic Dynamics Tunnel , 1982 .

[27]  R. H. Ricketts,et al.  Transonic pressure distributions on a rectangular supercritical wing oscillating in pitch , 1984 .

[28]  Jose A. Rivera,et al.  Contributions of Transonic Dynamics Tunnel Testing to Airplane Flutter Clearance , 2000 .

[29]  Robert M. Bennett,et al.  Test Cases for a Clipped Delta Wing with Pitching and Trailing-Edge Control Surface Oscillations , 1999 .

[30]  T. A. Byrdsong,et al.  Close-Range Photogrammetric Measurement of Static Deflections for an Aeroelastic Supercritical Wing , 1990 .

[31]  J. Edwards.  Transonic shock oscillations calculated with a new interactive boundary layer coupling method , 1993 .

[32]  Robert M. Bennett.  Test Cases for a Rectangular Supercritical Wing Undergoing Pitching Oscillations , 1999 .

[33]  Robert M. Bennett,et al.  A status report on a model for Benchmark active controls testing , 1991 .

[34]  Stanley R. Cole,et al.  Past, Present, and Future Capabilities of the Transonic Dynamics Tunnel from an Aeroelasticity Perspective , 2000 .

[35]  W. Ng,et al.  Cryogenic tunnel measurement of total temperature and pressure , 1986 .

[36]  Robert W. Hess,et al.  Steady and unsteady transonic pressure measurements on a clipped delta wing for pitching and control-surface oscillations , 1986 .

[37]  Robert M. Bennett,et al.  Experimental flutter boundaries with unsteady pressure distributions for the NACA 0012 Benchmark Model , 1991 .

[38]  J. B. Mcdevitt,et al.  Static and dynamic pressure measurements on a NACA 0012 airfoil in the Ames High Reynolds Number Facility , 1985 .