Effects of plan form, airfoil section, and angle of attack on the pressures along the base of blunt-trailing-edge wings at Mach numbers of 1.41, 1.62, and 1.96 Page: 4 of 54
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2 CONFIDENTIAL-JTh NACA RM L52D21
Maximum variations in average base pressures resulted from varia-
tions in wing sweep and taper and in Mach number. The Mach number com-
ponent normal to the wing leading edge appeared to be one of the more
fundamental parameters influencing variations of base pressure coeffi-
cient at Mach numbers of 1.41 and 1.62. At a Mach number of 1.96, how-
ever, the Mach number component normal to the wing trailing edge appeared
to be of greater importance.
Results obtained from previous base-pressure investigations by free-
flight, wind-tunnel, transonic-bump, and wing-flow techniques have been
summarized and compared with results of the present investigation. All
results were found to be in 'good general agreement.
Recent experimental investigations have shown that wings having
blunt-trailing-edge sections will in some cases have higher lift-curve
slopes, lower minimum drag, and higher maximum ratios of lift to drag
at supersonic speeds than corresponding wings having sharp-trailing-edge
sections (ref. 1). In consideration of these improved aerodynamic
characteristics, together with obvious structural advantages, blunt-
trailing-edge wings appear very promising for use at supersonic speeds.
Considerable experimental information on wing base pressures at Mach
numbers of 1.5 to 3.1 is presented in reference 2. Although limited
variations with spanwise location and angle of attack are included in
reference 2, most of the base pressures were measured near the midsemispan
position on rectangular wings of aspect ratio 3.0 and were obtained at
00 angle of attack. Limited data with similar restrictions for Mach
numbers of 0.6 to 1.6 are included in references 3, 4, and 5. For esti-
mations of wing base drag, considerably more information is needed con-
cerning the variation of base pressures with spanwise location, with
angle of attack, and with wing plan form.
As part of an investigation of wings with blunt-trailing-edge sections
at Mach numbers of 1.41, 1.62, and 1.96, base pressures have been measured
along the spans of 21 wings at angles of attack of 00 to 150. Results
of this base-pressure investigation are presented herein and include
representative effects of wing plan form and detailed effects of wing
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Goin, Kennith L. Effects of plan form, airfoil section, and angle of attack on the pressures along the base of blunt-trailing-edge wings at Mach numbers of 1.41, 1.62, and 1.96, report, September 16, 1952; (digital.library.unt.edu/ark:/67531/metadc59299/m1/4/: accessed July 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.