Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane Page: 2 of 19
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:
NACA RM No. L8E18a iiriiiW"ThW/u/or
SIllilllillBl ll IIIrh I4ll * 0 G
LATIOAwAL AFP - 3 1176 01436 6455 OUI.ICS
WIND-uINmL Bn mYoATo o E STB OF T HE JETIISONABLE
HOSE SECTION OF THE X-3 AIRPLANE
By Stanley H. Scher
Because previous work has indicated that jettisonable nose sections
of airplanes may be inherently unstable, and thus mey cause dangerous
centripetal accelerations on a pilot after jettisoning during high-speed
flight, an investigation has been conducted in the l ngley 20-foot
free-spinning tunnel to determine the behavior in descent of a model of
the jettisonable nose section of the Douglas 1-3 airplane. The effects
of varying the ceater-of -gravity position, of attaching fins of various
size, and of installing a stabilizing parachute were investigated.
In investigation the model descended with its front end
teamed -3~ above the horizontal and rotated about a vertical wind axis
while rolling about its longitudinal body axis. The nose section was
made to descend in a stable front-down attitude when stabilizing fins
were installed in conjunction with movement of the center of gravity
forward or when a stable parachute was attached to the model.
INTERODUTION
The NADA is conducting a general investigation of methods of pilot
escape from high-speed aircraft. One method that has been proposed for
the X-3 airplane and for several other recent designs is to jettison
the nose of the airplane at a break-off station immediately rearward of
the pilot; after the nose has been jettisoned and its speed has
decreased, the pilot would leave the nose section and descend with his
personal parachute. Spin-tunnel experience with models of Jettisonable
nose sections of airplanes (references 1 and 2) has indicated that the
noses may be inherently unstable, and when Jettisoned at high airspeeds
may undergo rapid rotations which may cause dangerous accelerations on
the pilot. The behavior of the Jettisoanable nose of the X-3 airplane
has been investigated at low speeds through tests of a 1 -scale model
23
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.
Scher, Stanley H. Wind-Tunnel Investigation of the Stability of the Jettisonable Nose Section of the X-3 Airplane, report, December 8, 1946; (https://digital.library.unt.edu/ark:/67531/metadc64133/m1/2/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.