Mass flow requirements for LFC wing designThe problem of determining optimum suction mass flow requirements for LFC wings is addressed. Some previous methods for predicting the extent of laminar flow over swept wings with suction are briefly reviewed. These range from the purely empirical to those utilizing tabulated linear stability computations. The present method is described. This method solves the linear, incompressible stability equations by spectral techniques. The maximum temporal amplification of boundary layer crossflow and 2-D disturbances is determined for waves of a given frequency. Group velocities are used to integrate these amplification rates along the wing to yield the logarithmic amplitude ratio or 'N factor' of the disturbance. The 'N factor' calibration of a computer code utilizing this method is described, using experimentally determined transition data. The method is shown to be as consistent as previously used 'fixed wavelength' methods.
Document ID
19770061471
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Srokowski, A. J. (NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, Va., United States)
Orszag, S. A. (MIT Cambridge, Mass., United States)
Date Acquired
August 9, 2013
Publication Date
August 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 77-1222
Meeting Information
Meeting: Aircraft Systems and Technology Meeting
Location: Seattle, WA
Start Date: August 22, 1977
End Date: August 24, 1977
Sponsors: American Institute of Aeronautics and Astronautics