Two-dimensional unsteady lift problems in supersonic flight Page: 12 of 13
This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and was provided to UNT Digital Library by the UNT Libraries Government Documents Department.
Extracted Text
The following text was automatically extracted from the image on this page using optical character recognition software:
REPORT .9451-NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
'I.
.0
'd
cc
4-
0-
cci
cc
0
E
c _(b) Ai=1.31.
FIGURE 7.-Concluded.
value calculated in the present report for 1=1.31. The
4m
results are plotted as functions of tj-= Sc to correspond with
the density parameter used by Jones. The correspondence
which was noted for the indicial lift functions with Mach
number replacing wing aspect ratio is still in evidence.0 80 /160 240
Wing density parameter, gS=2m/pScM
FIGURE 8.-Maximum increment in lift coefficient attained during flight through unit
sharp-edged gust for various values of free-stream Mach number.0 40 80 ia20 160 200 E 40
Wing density porcne fer, pj 47n/pSc
FiG RE 9.--Comrnparison of maximum increments in lift coellierents during flight through
sharp-edged gust between subsonic wing and supersonic wing.
FORCES DEVELOPED ON GIVEN WING
As an example of the uses to which the results just obtained
can be applied, consider an airplane with wing of plan form
such as the one shown in figure 2. Assume a wing loading
of 40 pounds per square foot, a chord length of 8 feet, and
let it be specified that the wing is flying at a Mach number
equal to 1.2 and that the wing is built to withstand forces
producing accelerations between -3 and 5 times gravita-
tional acceleration. It is proposed to find at what altitudes
the wing may be subjected safely to a gust possessing a
vertical velocity of 50 feet per second.
If F denotes the net lifting force on the wing,F= W+ Lg
(21)
where W is wing weight and L is the total lift produced by
the gust. If (ACL)max is the maximum increment in lift
coefficient attained in a unit gust and A is the acceleration8
Upcoming Pages
Here’s what’s next.
Search Inside
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.
Heaslet, Max A. & Lomax, Harvard. Two-dimensional unsteady lift problems in supersonic flight, report, December 5, 1947; (https://digital.library.unt.edu/ark:/67531/metadc60268/m1/12/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.