The design and construction of an advanced swept supercritical airfoil for commercial aircraft to be tested in a transonic wind tunnel is described. The swept LFC airfoil was designed for a given thickness ratio and lift coefficient, with emphasis placed on high critical Mach number with shock-free flow. It is compatible with satisfactory low speed and buffeting characteristics and minimizing the suction laminarization. Further emphasis was placed on achieving shock-free flow over a wide range of off-design conditions including trailing edge flap control. The requirements and design of the suction system and modifications to the Langley 8 foot transonic pressure tunnel is briefly described. Contouring of nonporous test section walls for free air simulation and flow quality improvements is included.
NASA Langley laminar flow control airfoil experiment
1982-03-01
Aufsatz (Konferenz)
Keine Angabe
Englisch
The NASA Langley laminar flow control airfoil experiment
NTRS | 1982
|The NASA Langley laminar flow control airfoil experiment
AIAA | 1982
|