Publikationsdatum:
2019-07-13
Beschreibung:
An experimental research program was conducted in the NASA Lewis Research Center 10 x 10 ft supersonic wind tunnel. The 2-D inlet model was designed to study the Mach 3.0 to 5.0 speed range for an over-under turbojet plus ramjet propulsion system. The model was extensively instrumented to provide both analytical code validation data as well as inlet performance information. Support studies for the program include flow field predictions with both 3-D parabolized Navier-Stokes (PNS) and 3-D full Navier-Stokes (FNS) analytical codes. Analytical predictions and experimental results are compared.
Schlagwort(e):
AIRCRAFT PROPULSION AND POWER
Materialart:
NASA-TM-102317
,
E-5011
,
NAS 1.15:102317
,
AIAA PAPER 89-2355
,
Joint Propulsion Conference; Jul 10, 1989 - Jul 12, 1989; Monterey, CA; United States
Format:
application/pdf
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