Publikationsdatum:
2011-08-16
Beschreibung:
The experiment was performed on the test section sidewall in a supersonic pressure tunnel. The boundary layer at the test station was surveyed in turn by each of 8 impact probes ranging in size from about 1.3 to 48 mm. The impact pressures measured by these probes were combined with the test section static pressure to calculate Mach numbers. Probe displacement effects were evaluated in terms of these Mach number values.
Schlagwort(e):
AERODYNAMICS
Materialart:
AIAA Journal; 10; Apr. 197
Format:
text
