Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane Page: 4 of 131
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NACA RM A9101 3
The effective downwash angle at the tail, the Mach number at the tail,
and the tail efficiency factor are presented herein.
COEFFTICIETlB AND SYMBOLS
The following coefficients are used in this report:
CL lift coefficient (lift)
CD drag coefficient ra
Cm pitching-moment coefficient about an axis normal to the plane of
symmetry passing through the quarter point of the wing mean
aerodnac chord itching moment)
aerodynamic chord qSc'
- total-pressure-loss coefficient H
q q
The following symbols are used in this report:
a speed of sound, feet per second
b twice the span of the semispan wing, feet
c local wing chord, feet
c' wing mean aerodynamic chord, chord through centroid of the
So c~dy
wing semispan plan form : b 2:
c dy
H local stagnation pressure in the region of the horizontal tail,
pounds per square foot.
Ho free-stream stagnation pressure, pounds per square foot
it angle of the stabilizer setting with respect to the wing-chord
plane, degrees
It tail length, distance from quarter point of the wing mean
aerodynamic chord to the quarter point of the horizontal-
tail mean aerodynamic chord, feet4
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Johnson, Ben H., Jr. & Rollins, Francis W. Investigation of a Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind Tunnel 5: Static Longitudinal Stability and Control Throughout the Subsonic Speed Range of a Semispan Model of a Supersonic Airplane, report, December 8, 1949; (https://digital.library.unt.edu/ark:/67531/metadc58320/m1/4/: accessed March 30, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.