Documents / FOIA release
roswell
Office of the Secretary of Defense · 993 pages · text from the file's own layer
The Roswell Report: Fact versus Fiction in the New Mexico Desert was published in 1995 by Headquarters United States Air Force. It was written in response to Representative Steven H. Schiff's request and a General Accounting Office audit, and it contains Col. Richard L. Weaver's report and 1st Lt. James McAndrew's synopsis, along with attachments, appendices and photographs. The report says researchers found no evidence of an extraterrestrial craft or crew. It concludes that the 1947 debris came from a Project MOGUL balloon train.
“Sea”26 pages
- p. 129 …6099 2 HQ AMC WRIGHT PAT
342-seA-6191 CAMBRIDGE LABS
342-A~ AMC HQ WRIGHT…
- p. 228 …overhead and followed the
balloons out to sea. I have no idea about the results that…
- p. 235 …the regular 334
that we had at sea level. From that they could deduce the
temperature…
- p. 279 …actually located on the jurisdictional lines between
Sea Girt and Springlake, New Jersey. It was an…
- p. 280 …The Sea Girt Inn?
A: Exactly. That's where John had his office, and I was…
- p. 400 …alone 1a about 24,000.m1lea at sea level,
aDd about '500 allea at 45,000…
- p. 407 …five (25) feet at their ls.rgest sea-level diameter. The sonic
unit was a combination…
- p. 466 …hour when one-fifth inf~ated at sea level).
One other type of balloon which has…
- p. 490 …Let us, then, compare the rate of
leakage at any given altitude with leakage at sea…
- p. 492 …The leakage at any
altitude may be expressed as a function of leakage at sea
level…
- p. 493 Comparing rete of leakage at 40,000 feet with leakage at
sea level:
~ 188 .u§. - 0…
- p. 495 …It a 20-foot diameter balloon~ full were tested at
10
sea level and found to…
- p. 496 …At sea level this is equivalent to 5.32 ~r. for a 20-foot
diameter balloon…
- p. 502 …Using the rules of subsonic aerodynamics, Picard
suggests that air at sea level escaping at 1333…
- p. 503 …sea level (psi)
escape velocity of air to produce back pressure
of 1 atmosphere at sea…
- p. 520 …to about 20 millibars and increased to sea-level pressure at
different temperatures.
The most comprehensive…
- p. 654 …The height above mean sea level as determined fram
pressure measurements used in this work with…
- p. 686 …to a thtmble
a.nd attached to re1n forced pCltches
at alterna.te .sea.m.s…
- p. 688 …lQr9e
Ba.lloo n ~hould trQin de .sea nd to 101000'.
6 each.-Gene ral M1lls…
- p. 736 …point
at which the radiosonde reaches the sea surface.
2. Earlier attempts
There have been numerous…
- p. 737 …The
balloons floated between the surface and 30,000 ft
above sea level; those which reached…
- p. 801 …Vet Gifford ;.;ho has
0 0' sea rescue boat this project is planning to use. Stayed…
- p. 816 …Worzel
working on gravity at sea. Saw Geo Woollard and the Ryders. Woollard after Guggenheim
fellowship…
- p. 887 …the launching site is
markedly different from sea level, a shift in this curve
is needed…
- p. 925 …balloon
at all times with respect to sea level. On this curve also
it is customary…
- p. 933 …The height above ~ean sea level as determined
from pressure measurements used in this work
with…
This relationship between loss of lift end loss of superheat is
substantiated by analysis of Flight 94. From the rate of descent
the unbalance {~sing the equation of Clerke and Korff, see page 3.3 )
is in the neighborhood of 5 kilograms. Although there 'WJI.S no
temperature measurement on this flight, a previous flight of
this type indicated a superheat of approximately 400C. By equation
{10), with a gross load of 52 kg., the unbalance caused by loss
of all of this superheat would be 9.7 kg. It is believed thet
ventilation past the balloon during a low velocity descent before
operation of the ballast mechanism caused loss of superheat. Since
this loss caused greater descent, and thus more ventilation, super-
heat was lost. An enormous rete of ballast flow would have been
required to check descent.
D. Adiabatic Lapse Rate
One of the causes of temperature difference between the lifting gas
and free air during rise or descent of balloon systems is the
difference in lapse rates of eir end the lifting gas. The adiabatic
lepse rate is that temperature change caused by adiabatic ex-
pansion or compression of a gas during ascent or descent through a
given vertice.l distance. The actual lapse rate of the lifting gas
is the adiabatic lapse rate plus the effects of conduction and
radiation. The adiabatic lapse rate is defined as:
{1)
where:
LR = -¥p
A = 2.39 x 108 col I erg
Cp = specific heat at constant pressure
g = acceleration caused by gravity
In the met-ric system for helium, ( Cp = 1.25 0 ~'~m ) '
LR • 980 X 2.39 X 10-s
-- 1.2! =
or:
The e.diebatic lapse rete for e ir, ( Cp = 0.239 col ) :
OC/gm
LR = 980 • 2.39 • 10·3 _ 9_8 oct km
0.239 =or:
LR = - 2.98oC/IOOO ft
-38- About this file
FOIA release, from the osd collection. The PDF is mirrored here; the original link is under it. 993 pages are in the text index: search them above, or from the library's search.