Publication Date:
2019-06-28
Description:
An investigation was conducted in the static-test facility of the Langley 16-Foot Transonic Tunnel to determine the internal performance of a high-aspect-ratio nonaxisymmetric nozzle with five circular-to-rectangular transition ducts of varying design. Nozzle pressure ratio was varied from 1.5 to 5.3, and nozzle performance parameters were recorded.
Keywords:
AIRCRAFT PROPULSION AND POWER
Type:
NASA-TP-2534
,
L-15874
,
NAS 1.60:2534
Format:
application/pdf
Permalink