Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10 Page: 4 of 37
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 A53D02 3
CN normal force coefficient, normal force
M free-stream Mach number
Pb base pressure, lb/sq ft
q free-stream dynamic pressure, lb/sq ft
R Reynolds number based on free-stream properties and model
RT transition Reynolds number based on free-stream properties and
length of run of the laminar boundary layer
t time, see
a, angle of attack, radians
a mean angle of attack, , radians
1, 2; intervals of time or distance between stations 1 and 2, 1 and
1,s; 3, 2 and 3, etc.
TEST TECHNIQUE AND CONDITIONS
The investigation was conducted in the Ames supersonic free-flight
wind tunnel. In this facility the model is launched from a gun mounted
in the wind-tunnel diffuser and flies upstream through the test section.
Mach numbers below approximately 4 are obtained by firing the model
through still air. Higher Mach numbers are obtained by firing through
the supersonic air stream of the wind tunnel. A detailed discussion of
the test technique will be found in reference 1.
The model tested is shown in figure 1(a). The body has an ogive
nose tangent to a circular-cylindrical afterbody. The fineness ratio of
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.
James, Carlton S. & Carros, Robert J. Experimental investigation of the zero-lift drag of a fin-stabilized body of fineness ratio 10 at Mach numbers between 0.6 and 10, report, June 11, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59730/m1/4/: accessed March 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.