Method for estimating lift interference of wing-body combinations at supersonic speeds Page: 4 of 45
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 A1J04 3
A aspect ratio of exposed wing panels joined together
c mean aerodynamic chord, inches
CL lift coefficient based on exposed wing area
CLu lift-curve slope based on exposed wing area
Cr chord at wing-body juncture, inches
Ct wing tip chord, inches
Cy wing chord at spanwise distance y from body axis, inches
d body diameter, inches
E complete elliptic integral of second kind
K 'ratio of lift of combination to that of wing alone
KB ratio of lift carried by body of combination to lift acting on
KW ratio of lift carried by wing of combination to lift acting on
L lift force, pounds
ia afterbody length, inches
if forebody length, inches
M free-stream Mach number
m cotangent of leading-edge sweep angle
Q free-stream dynamic pressure, pounds per square inch
r body radius, inches
R Reynolds number based on mean aerodynamic chord
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.
Nielsen, Jack N & Kaattari, George E. Method for estimating lift interference of wing-body combinations at supersonic speeds, report, December 31, 1951; (digital.library.unt.edu/ark:/67531/metadc59104/m1/4/: accessed October 23, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.