Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane Page: 3 of 51
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NACA M No. L7D09
Langley 19-foot pressure tunnel to determine s ome of the aerodynamic
characteristics of a 1/8.33-scale powered model of the XF-12 airplane.
The results of,, the investigations to determine the static lateral
and loJgitudinal stability:.:chaa.acteristios are presented in refer-
ences I and 2, respectively; the stalling characteristics are included
in reference 2.
In order to obtain information relative to the design of the
vertical and horizontal tail surfaces, dynamic pressure, sidewash,
and downwash surveys were made in the vicinity of the enpennage. The
vertical-tail surveys were made through a range of yaw angles of 1200
at a high and a low angle of attack, and data pertinent to the
horizontal-tail design were obtained over a fairly wide range of
angles of attack for the unyawed condition. Several power and flap
conditions were investigated.
- COEFFICIENTS AND SYMBOLS
The coefficients and symbols used are defined as follows:
CL lift coefficient (L/qS)
To effective thrust coefficient (T/2qD2)
QC torque coefficient (Q/2qD3)
L lift (-Z)
q free-stream dynamic pressure (p2)
p mass density of air
coefficient of viscosity of air
V free-stream velocity.
T effective thrust of one propeller
D propeller diameter_.
Q torque of one propeller
a angle of attack of wing root chord line
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Foster, Gerald V. Air-Stream Surveys in the Vicinity of the Tail of a 1/8.33-Scale Powered Model of the Republic XF-12 Airplane, report, April 8, 1947; (digital.library.unt.edu/ark:/67531/metadc64217/m1/3/: accessed October 22, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.