Publication Date:
2019-06-28
Description:
The wind tunnel tests were conducted both with and without boundary layer trips at Mach 3 and nominal free stream Reynolds numbers per meter ranging from 3.3 x 10 the 6th power. Instrumentation consisted of pressure orifices, thermocouples, a boundary layer pitot pressure rake, and a floating element skin friction balance. Measurements from both wind tunnel and flight were compared with existing engineering prediction methods.
Keywords:
AERODYNAMICS
Type:
NASA-TP-1789
,
L-14044
Format:
application/pdf