Flight investigation of the supersonic area rule for a straight wing-body configuration at Mach numbers between 0.8 and 1.5 Page: 2 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:
NASA Technical Library
NACA RM L55C09 CONFIDENTIAL IlllllIlllll111 l 1111
3 1176 01437 2073
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
FLIGHT INVESTIGATION OF THE SUPERSONIC AREA RULE
FOR A STRAIGHT WING-BODY CONFIGURATION AT
MACH NUMBERS BETWEEN 0.8 AND 1.5
By Sherwood Hoffman, Austin L. Wolff, and Maxime A. Faget
An investigation of the supersonic area rule has been conducted by
rocket-propelled model tests of zero-lift models of a straight wing-
body configuration through a range of Mach number from 0.8 to 1.5 and
Reynolds number from 5 x 106 to 12 x 106. The body of the basic con-
figuration was modified with axial symmetrical indentations according
to area-rule considerations for low wave drag at design Mach numbers of
1.10 and 1.41. The indentations were designed using a short method
(given in appendix) that greatly simplified the work. Each configura-
tion had at its respective design Mach number the same distribution of
cross-sectional area as the basic body alone. The basic body was
parabolic having a frontal area equal to 0.0606 that of the total wing
plan-form area. The wing had an aspect ratio of 3.04, taper ratio of
0.394, 00 of sweep along the 75-percent chord line, and an NACA 65A004.5
airfoil section in the free-stream direction.
Both the Mach number 1.10 and 1.41 indentations reduced the wave
drag of the basic configuration at transonic speeds with the greater
reduction being obtained from the Mach number 1.10 indentation. The
beneficial effects from the indentations decreased with increasing
Mach number until Mach number 1.3, above which no benefits were obtained
from either indentation. Both indented configurations had the same drag-
rise above Mach number 1.15. The theoretical wave drags of the configu-
rations were useful in showing the relative merits of the different
The transonic area rule of reference 1 provides a simple and effec-
tive means for designing high-speed aircraft for low wave drag near the
speed of sound. Investigations of the transonic area rule (refs. 1 to 11)
_ ___ __
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; Wolff, Austin L. & Faget, Maxime A. Flight investigation of the supersonic area rule for a straight wing-body configuration at Mach numbers between 0.8 and 1.5, report, April 29, 1955; (digital.library.unt.edu/ark:/67531/metadc61224/m1/2/: accessed October 20, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.