@Rodal
Thanks for the pointers. I was looking for that deck that you linked to on NTRS. I believe Dr. White used it in a presentation I saw this year. Anyway, the most interesting thing about that deck is it seems like there is mounting evidence that there really is something here. Though what I really wonder about is if the Boeing SFE test article had such good results, what happened to it? are there any future plans for further testing on that particular design. I cannot seem to find any information via google or NTRS documenting the test campaign that Boeing device is said to be apart of. I hope it is not covered by NDA...
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Here I compare the experimentally measured Thrust Force and the Specific Force (defined as Thrust Force / Input Electric Power) for the different devices tested at NASA Eagleworks.
From this comparison it appears that the latest round of tested devices (the Cannae and the Fustrum Cavity) have among the lowest measured Thrust Force and the lowest Specific Force.
Since what we are looking for is the highest Thrust Force and the highest Specific Force possible, why is the latest discussion in this forum concentrating on the performance of the latest round of tested devices, when they appear to have among the lowest measured thrust forces and the lowest specific force ?
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Referring to slide 40 of
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20140000851.pdf:
The largest THRUST force measured is for Shawyer/SPR Ltd.'s microwave device:
16 to 170 mN
However, it also happens to have among the LOWEST Specific Force (in that slide, but still significantly higher than the specific forces measured in the latest round for the Cannae and Tapered Frustum cavity -see below):
0.02 to 0.4 N/kW
The largest SPECIFIC FORCE measured is for the Boeing/DARPA device:
1 to 20 N/kW but the upper range was produced only by an unexplained anomalous thrust (one out of 8 pulses)
the average thrust was 3N/kW
but (when compared with the Shawyer/SPR's device numbers above), with very small thrust force: 20 to 110 uN (again, the 110 uN is for one anomalous thrust force out of 8 pulses, the average of the other ones is 20 uN)
Also notice that Dr. White writes
<<The magnitude of the [Boeing/DARPA] thrust scaled approximately with the cube of the input voltage>>
and
<<The magnitude of the [Boeing/DARPA] thrust is dependent on the AC content of the turn-on and turn-off pulse>>
and I notice:
the Boeing/DARPA measurements show a sudden impulse of very short duration instead of the practically square pulses measured with the latest tested devices (Cannae and (Fustrum) Tapered Cavity).
It is NOT clear to me whether Dr. White is reporting on measurements his Eagleworks lab conducted on the Shawyer/SPR Ltd.'s device, or whether he is reporting measurements made
elsewhere with the Shawyer/SPR Ltd.'s device.
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For the latest round of NASA Eagleworks measurements (in the paper "Anomalous Thrust Production from an RF Test Device Measured on a Low-Thrust Torsion Pendulum"):
Cannae Testing:
THRUST Force average: 40 uN
Specific Force: 0.0014 N/kW
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Tapered (Frustum) Cavity Testing:
THRUST Force average: 50 to 90 uN
Specific Force: 0.003 N/kW to 0.0054 N/kW
Where I obtained the "Specific Force" by dividing the Thrust Force by the Input Electric Power (for example, for the Tapered Cavity 16.9 Watts electric).
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Everybody:
please take a look at this comparison, and provide some feedback as to why the latest discussion in this forum is concentrating on the performance of the latest round of tested devices, when they appear to have among the lowest measured thrust forces and the lowest specific force ?Have I misinterpreted something in the above comparison?
If so, how is the Specific Force calculated in slide 40 of Dr. White's presentation in the above link and elsewhere in his papers?
Also notice that <<Figure 25. 2MW NEP (90t spacecraft) Crewed Titan/Enceladus Mission with 0.4N/kWe thrust to power>> in the "Anomalous thrust..." paper uses 0.4N/kW (compare this with the Boeing/DARPA figure given in slide 40 above, which is 1 to 20 N/kW). Of course I do understand that the Crewed Titan/Enceladus Mission must have assumed an amount of thrust much larger than the minute thrust measured at Eagleworks for the Boeing/DARPA device

, and that must be also the object of your criticism (the assumption that the devices can be eventually scaled up to produce required thrust and specific forces)