I'd never seen the flag move video before.
My first thought was, "That IS interesting!"
My second thought was, "He says it's 'flapping' in the breeze and is being very dramatic about it. That's hyperbolic to say the least, but it clearly did swivel a bit, like a little sail picking up some amount of energy."
My third thought was, "I wonder what could cause that?"
My fourth thought was, "Was there was any out-gassing from the LEM while the astronauts were inside"?
Turns out that there indeed was. It was even recorded spiking at very moment of the flag motion when a valve was opened on the LEM.
Case closed? Of course not! The videographer's whole reason for existing appears to be very much wrapped
I concur with the first 3 steps but would not stop there. Why ? Because taking this position one is open to the argument “You
assume it was the depressurization activity that caused the movement?”. In a debate the opposing side would say “Prove it is due to depressurization.”
What is needed is numbers. Without numbers it is like going to a gunfight with no gun. To get numbers takes knowledge, work and time.
Seeing the flag moving tells me
THERE IS SOME KIND of FORCE on it but by just looking at the video I can not identify its source. I can guess but then that is all it is, an educated guess.
Thus what is needed it to established the possible source of this force and quantify it. Is it from the depressurization activity or is it not ? That is the question here. Simply to state there was a depressurization is not enough.
So I would continue as follows.
5) Watching the video I do NOT know at what point in their schedule this is all happening. Yes there is a clue about the PLSS being readied to be dumped but I needed to know how movement of the flag swinging syncs in with the schedule. Without the check the possibility exists that depressurization has ended and after this the flag is moving.
The clue for me is this transmission, “Okay, Houston. XXX Relief is now in Auto. The “XXX” will be know in a few lines. Taking that text into Google I found the transcription of the conversations here,
The transcript shows us,
136:20:50 Shepard: Okay, Houston. Suit Circuit Relief is now in Auto.
In the video this happens at about 1:52.
So we have
136:19:09 Shepard: Houston, Antares.
We're depressing the cabin for jettison now.
136:19:12 Engle: Okay, Al. We're watching that and it's looking good. Suits are looking good. (Long Pause) Okay, Antares. Could you verify Suit (Circuit) Relief (valve) in Auto, please? (Long Pause)
Then these parts are in the video,
0:57 - 1st appearance of the Flag
1:11 - Flag disappears
1:18 - Apollo conv. --->
136:20:14 Okay, Antares. Could you verify Suit ....
1:32 - 2nd appearance of Flag
1:52 - Apollo conv. --->
136:20:50 Shepard: Okay, Houston.
Suit Circuit Relief is now in Auto.
1:55 - Apollo conv. --->
136:20:54 Engle: Okay; thank you, Al.
2:05 - Flag disappears
3:42 to 3:51 - more appearance/disappearance of the Flag
3:52 - Final Flag disappearance
This part is not in the video
136:23:40 Shepard: Okay, Houston. We're going to jettison now.
So from NASA record I know that a depressurization was happening. The record also explains what we are viewing in the video. From this I am able to estimate when the decompression of the cabin started and ended.
Start,
136:19:09 Shepard: Houston, Antares. We're depressing the cabin for jettison now.
End
136:23:40 Shepard: Okay, Houston. We're going to jettison now.
I am estimating that it took them 3 1/2 minutes to depressurize the LEM.
From dump valve specs I find,
“With a bacterial filter installed, the forward hatch valve could dump pressure from 5.0 to 0.08 psia in 310 seconds without cabin oxygen inflow; without a filter in place, either valve could dump cabin pressure to 0.08 psia in 180 seconds; “
I will stick with 3 1/2 min as the time to depressurize.
6) To generate a “wind” which will strike the flag you need a flow stream. Thus we need an estimation of the flow rate, Volume/Time.
The following is given by NASA, “ASCENT STAGE - The ascent stage, control center of the LM, is comprised of three main areas: crew compartment, midsection, and equipment bay. The crew compartment and midsection make up the cabin, which has an overall volume of 235 cubic feet. The basic structure is primarily aluminum alloy; titanium is used for fittings and fasteners. “
V_cabin = 235 cubic feet
“While the LM has a
cabin pressure of 3.5
psi on the Moon. “
So the potential pressure differential cabin - Space to drive the oxygen out is ~3.5 psi.
Warning: If you do not have a dark sense of humor don't go,
Gases
So we know the Ascent Stage has 235 ft3 of oxygen at 3.5 psi that was released over a period of 3 1/2 minutes. Bar stool calculation gives 1.1 ft3/sec. but the rate is sure to be much higher as the other side is open to vacuum.
To get a feel for these numbers I bled my compressor in the basement to a pressure of around 7 psi and let it loose. What I got was breeze a little stronger than if I vigorously blew the air from my mouth with the hand a foot away from the nozzle. OK, everything on the Moon is happening in vacuum so that physical experiment doesn't count.
7) Next we need to locate the venting point(s) for the Ascent Stage ?
First dump valve found
in the front (AFT) section where the LEM windows are located, here
second located
on top of the LEM is shown here
5) The next crucial issue is geometry. Where is the flag relative to these vents ?
I think it is safe to forget about the top vent but if anyone has a problem with that extend what I have done.
To locate the flag relative to AFT vent we look in photos. I found a photo around the end of EVA-2,
The flag looks to be perpendicular to the cabin hatch. What we lack is distances. Vertical distance to the depressurization valve measured from surface is about 14 ft .
Lateral distance I estimated from photo and LEM diagram as around 23 ft. So straight line distance valve-flag is about 27 ft.
Seeing the numbers above I did another experiment with my compressor to checked at what distance I would stop feeling the “wind” from the compressor at 7 psi. Try the experiment to experience the answer.
7) The top vent can not be the source of the disturbance for the obvious reasons that it is looking upward into space. The second AFT vent is another matter. We need some numbers to access the pressure disturbance from such an event.
But this is not a trivial problem as we are venting into vacuum through hole(s) (choke point) in the dump valve seen here,
The phenomena describing this in fluid dynamics is call Ventury Effect.
So basically we are looking at a small rocket motor in terms of fluid dynamics. But this “rocket engine” has 3.5 psi behind it.
So where am I going with this ? Listen to this lady at 2 min mark in the video here where she expalains why the plume is not seen at lift off.
video
The effect of expanded plum size in vacuum was also used to explaining why the rocket engine did not kick up a
dust storm on the Moon. Plume was said to be very large hence the pressure of the plume on the surface was just like a
“gentle breeze”.
So what's good for the goose is good for the gander. If the rocket plume expands I would expect the jet of oxygen coming out of the depressurizing cabin at 3.5 psi to behave similarly. Expanding in ever widening "plume" move those 27 ft. toward the flag in zero pressure space. As this would be happening, those oxygen molecules would be fly off in all directions creating a “gentle breeze” on the
metal pole and flag.
So intuition suggest to me that if a rocket engine's large plume
does not generate a huge dust storm as the pads probes contact the lunar surface to shut it down then the dump port releasing air at 3.5 psi cabin pressure will not sway a flag on a metal rod assembly pointed
nearly perpendicular to the ports while overcoming the the frictional forces in flag assembly at a distance of about 27 ft. Looking at the engineering diagrams of the flag it seems that it rotates with the upper pole assemble inserted inside the central pole assemble and not around the hinge.
However
intuition in itself does not prove that it can't happen. So this is not a closed case. Perhaps the air stream configured itself such that it went straight for the flag. I have no idea. But there is a way to find out.
This could be solved by simulating the depressurizing operation by using a computational fluid dynamic simulator. Here we can see how results for something like this would look,
The simulator would return velocity field, density field , etc in the area of the flag. One would then be able to calculate the Forces acting on the flag assembly.
Bad news is that I do not have a simulator that can do this and I don't think it would do any good if I had one and did this work. Why ? The argument would go on as usual
Have I proved that the depressurization was not the reason for why the flag is swinging ? No.
But I have however outlined how the problem looks from a technical point of view. What orders of mangnitude the numbers we are dealing if the dumping of oxygen is the source of the Force.
The same problem occurs with the Notre Dame fire. One can scream all day long that it was not cigarette butts or an electric short but that will not prove
that that could not be the cause. Numbers obtained from good science are another matter but then who likes to calculate numbers ?
Such is life in the Conspiracy World.