5 research outputs found
An investigation of wind tunnel wall effects at high Mach numbers
This paper presents the results of an investigation of
wind tunnel wall interference in a two-dimensional wind tunnel
at high Mach numbers. The results are presented in the form of
curves of lift coefficient versus the ratio of model chord to
tunnel height, as functions of Mach number and angle of attack.
The investigation was carried out by the authors at the
Guggenheim Aeronautical Laboratory of the California Institute
of Technology during the school year 1944-45.
Tests were carried out on the NACA low drag airfoil
section 65,1-012 at Mach numbers from .60 to .80, and angles of
attack of from 1 to 3 degrees. Models were 1", 2", 4" and 6"
chord, giving values of the chord to tunnel height ration of .1
to .6. Schlieren photographs were made of shock waves where they
occurred.</p