Zero-length, slotted-lip inlet for subsonic military aircraftZero-length, slotted-lip inlet performance and associated fan blade stresses were determined during model tests using a 20-inch diameter fan simulator in the NASA-LeRC 9- by 15-foot low-speed wind tunnel. The model configuration variables consisted of inlet contraction ratio, slot width, circumferential extent of slot fillers, and length of a constant area section between the inlet throat and fan face. Inlet configurations having contraction ratios of 1.2 and 1.3 satisfied all critical low-speed inlet operating requirements for a fixed horizontal nacelle and tilt-nacelle-type subsonic V/STOL aircraft, respectively. Relative to a conventional axisymmetric tilt-nacelle inlet, the zero-length, slotted-lip inlet has a 27-percent smaller inlet lip contraction ratio, an 83-percent shorter total length, and a 5-percent smaller maximum cowl diameter.
Document ID
19800057033
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Glasgow, E. R. (Lockheed-California Co. Burbank, CA, United States)
Beck, W. E. (Lockheed-California Co. Burbank, Calif., United States)
Woollett, R. R. (NASA Lewis Research Center Cleveland, Ohio, United States)