Numerical design of the contoured wind-tunnel liner for the NASA swept-wing LFC testA contoured, nonporous, wind-tunnel liner has been designed in order to simulate a free-flight infinite yawed-wing, transonic-flow condition about a large-chord, supercritical-section, laminar-flow-control (LFC), swept-wing test panel. The numerical procedure developed for this aerodynamic liner design is based upon the simple idea of streamlining and incorporates several existing transonic and boundary-layer analysis codes. A summary of the entire procedure is presented to indicate: what was done and why, the sequence of steps, and the overall data flow. The liner is being installed in the NASA Langley 8-Foot Transonic Pressure Tunnel (TPT). Test results indicating the aerodynamic performance of the liner are not yet available; thus, the liner design results given here are examples of the calculated requirements and the hardware implementation.
Document ID
19820041121
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Newman, P. A. (NASA Langley Research Center Hampton, VA, United States)
Anderson, E. C. (NASA Langley Research Center Hampton, VA, United States)
Peterson, J. B., Jr. (NASA Langley Research Center Hampton, VA, United States)