Investigation of a canard missile configuration (NACA RM-4) in the Langley 9-inch supersonic tunnel at Mach numbers of 1.62 and 1.93 Page: 4 of 25
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to Digital Library by the UNT Libraries Government Documents Department.
The following text was automatically extracted from the image on this page using optical character recognition software:
NACA RM L54E20
e pitch canard fins
r yaw canard fins
0, 45 angle between a plane through opposite canard-fin panels and
a plane through opposite wing panels
APPARATUS AND MODELS
The Langley 9-inch supersonic tunnel is a closed-return, direct-
drive type in which the pressure and the humidity are controlled. The
test Mach number is varied by means of interchangeable nozzle blocks
forming test sections approximately 9 inches square. Eleven fine-mesh
turbulence-damping screens are provided in the settling chamber ahead
of the nozzles. During the tests the amount of water vapor in the tunnel
air was kept at sufficiently low values so that the effects of condensa-
tion in the supersonic nozzle were negligible.
A drawing of the model giving the pertinent dimensions is shown in
figure 1 and a photograph of the model, in figure 2. The sting and
sting-windshield arrangement used in these tests is shown in figure 3.
At each angle of attack, the model, sting, and sting windshield were
translated across the tunnel so that a fixed point on the model could
be kept on the center line of the tunnel. Throughout the tests the gap
between the rear of the model and the movable windshield was maintained
at less than 0.012 inch.
Measurements of lift, drag, and pitching moment were made by means
of external self-balancing mechanical scales through an angle-of-attack
range of -50 to 150 for deflections of the canard fins of 00 5, 60,
100, and 150 and angles of roll of 00, 150, 300, and 450. The model was
tested both with the wings and canard fins inline and with the canard
fins interdigitated 450 with respect to the wings. An optical system
employing a small mirror mounted in the model was used to measure angles
of attack. Measurements were made of the pressure in the sting-shield-
and-balance enclosing box (tests have shown this pressure to be equal to
the model base pressure) and the drag results were corrected to the con-
dition of base pressure equal to stream static pressure.
_ I _ ~ _ ~__ __ ~
Here’s what’s next.
This report can be searched. Note: Results may vary based on the legibility of text within the document.
Tools / Downloads
Get a copy of this page or view the extracted text.
Citing and Sharing
Basic information for referencing this web page. We also provide extended guidance on usage rights, references, copying or embedding.
Reference the current page of this Report.
Grigsby, Carl E. Investigation of a canard missile configuration (NACA RM-4) in the Langley 9-inch supersonic tunnel at Mach numbers of 1.62 and 1.93, report, June 24, 1954; (digital.library.unt.edu/ark:/67531/metadc60099/m1/4/: accessed September 23, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.