The effect of nacelle combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3 Page: 4 of 24
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 L53E25
The wing had a sweepback angle of 4O5 along the quarter-chord line,
an aspect ratio of 6.0 (based on total wing plan-form area), a taper
ratio of 0.6, and an NACA 65A009 airfoil section in the free-stream
direction. The leading edge of the wing intersected the fuselage con-
tour at the maximum-diameter station. The fuselage fineness ratio was
10.0 and the ratio of total wing plan-form area to fuselage frontal
area was 16.0.
The single-engine nacelle (fig. 2(a)) was a solid body of revolu-
tion having a nose plug, an NACA 1-50-250 nose-inlet profile, a cylin-
drical midsection, and an afterbody with the proportions of form 111
(ref. 1). The fineness ratio of this single-engine solid nacelle was
9.66. The twin-engine nacelle shown in figure 2(b) was formed by placing
two single-engine nacelles tangent to each other along the cylindrical
portion and fairing between them with straight line elements. The large
nacelle, which had a fineness ratio of 8.56 (fig. 2(c)), was formed by
scaling up the coordinates of the inlet and afterbody of the single-
engine nacelle by a factor of 1.5 and leaving the cylindrical section
the same length as was used for the single-engine nacelle.
For convenience, information on the models presented in this paper
is tabulated below to indicate the nacelles used and the nacelle posi-
tions. The semispan locations are measured between the fuselage and
nacelle center lines in percent of the semispan. The chordwise loca-
tions are measured along the nacelle center line between the nacelle
nose and wing maximum thickness (0.4c) in percent of the mean aerodynamic
chord. All the nacelles were symmetrically mounted on the wing.
Model Nacelle location, lcn
percent b/2 perM.A.C.ent
A Twin-engine 19 ll6
B Large 20 165
C Large 94 163
D Single-engine 18 and 96 116 and 116
E (ref. 2) Single-engine 18 116
F (ref. a) Single-engine 96 116
G (ref. i) None --
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.
Hoffman, Sherwood & Pepper, William B., Jr. The effect of nacelle combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3, report, June 22, 1953; (https://digital.library.unt.edu/ark:/67531/metadc59629/m1/4/: accessed April 18, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.