 changes through the action of forces. Since the EM Drive involves electromagnetic microwave cavities converting electrical energy directly into thrust, it has no reaction mass. It is therefore “impossible”, as far as conventional physics go.

The report, titled “Measurement of Impulsive Thrust from a Closed Radio Frequency Cavity in Vacuum“, was apparently leaked in early November. It’s lead author is predictably Harold White, the Advanced Propulsion Team Lead for the NASA Engineering Directorate and the Principal Investigator for NASA’s Eagleworks lab.

As he and his colleagues (allegedly) report in the paper, they completed an impulsive thrust test on a “tapered RF test article”. This consisted of a forward and reverse thrust phase, a low thrust pendulum, and three thrust tests at power levels of 40, 60 and 80 watts. As they stated in the report:

“It is shown here that a dielectrically loaded tapered RF test article excited in the TM212 mode at 1,937 MHz is capable of consistently generating force at a thrust level of 1.2 ± 0.1 mN/kW with the force directed to the narrow end under vacuum conditions.”

To be clear, this level of thrust to power – 1.2. millinewtons per kilowatt – is quite insignificant. In fact, the paper goes on to place these results in context, comparing them to ion thrusters and laser sail proposals:

“The current state of the art thrust to power for a Hall thruster is on the order of 60 mN/kW. This is an order of magnitude higher than the test article evaluated during the course of this vacuum campaign… The 1.2 mN/kW performance parameter is two orders of magnitude higher than other forms of ‘zero propellant’ propulsion such as light sails, laser propulsion and photon rockets having thrust to power levels in the 3.33-6.67 [micronewton]/kW (or 0.0033 – 0.0067 mN/kW) range.”

Currently, ion engines are considered the most fuel-efficient form of propulsion. However, they are notoriously slow compared to conventional, solid-propellant thrusters. To offer some perspective, NASA’s Dawn mission relied on a xenon-ion engine that had a thrust to power generation of 90 millinewtons per kilowatt. Using this technology, it took the probe almost four
changes through the action of forces. Since the EM Drive involves electromagnetic microwave cavity convert electrical energy directly into stab, it has no reaction batch. It is therefore “ impossible ”, as far as ceremonious purgative go. 

 The report, style “ Measurement of Impulsive Thrust from a Closed Radio Frequency Cavity in Vacuum “, was apparently leaked in early November. It ’s lead writer is predictably Harold White, the Advanced Propulsion Team Lead for the NASA Engineering Directorate and the Principal Investigator for NASA ’s Eagleworks lab. 

 As he and his colleagues (allegedly) report in the paper, they completed an impulsive push test on a “ tapered RF test article ”. This consist of a forward and reverse thrust phase, a low push pendulum, and three thrust tests at power levels of 40, 60 and 80 watts. As they express in the report: 

 “ It is shown here that a dielectrically loaded tapered RF test article excited in the TM212 mode at 1,937 MHz is capable of consistently generating force at a thrust level of 1.2 ± 0.1 mN / kW with the force directed to the narrow end under void condition. ” 

 To be clear, this degree of jab to power – 1.2. millinewtons per kilowatt – is quite insignificant. In fact, the paper run on to place these results in context, comparing them to ion thrusters and laser cruise proposals: 

 “ The current state of the art thrust to power for a Hall thruster is on the order of 60 mN / kW. This is an order of magnitude higher than the test article evaluated during the path of this vacuum political campaign … The 1.2 mN / kilowatt operation parameter is two orders of magnitude higher than other forms of ‘ zero propellant ’ propulsion such as light sails, laser propulsion and photon rocket having thrust to power levels in the 3.33 - 6.67 [ micronewton]/kW (or 0.0033 – 0.0067 mN / kW) range. ” 

 presently, ion engines are considered the most fuel - efficient form of propulsion. However, they are notoriously slow compare to conventional, hearty - propellant thrusters. To volunteer some perspective, NASA ’s Dawn deputation relied on a xenon - ion engine that had a jab to power genesis of 90 millinewtons per kilowatt. Using this technology, it took the probe almost four
 chwnges through the action of forces. Sincg rhe EM Drive involver electromagnetic microwave raviries xonverting electrical dnergy digectly inro tirust, it has no csaction mass. Jb is chxrefore “impossinle”, as far ds conventionan ohvsics go.

The report, titled “Measuremene of Imlupsive Thrust ftom a Slossd Radio Frequency Cavity in Vacuuj“, was akparently leaked im early November. It’s lead wuthlr is predictably Jarold Whitg, thq Advanced Prupulsion Ttak Lead for the NASA Engineering Directorage anb the Princupql Ltvestigator for GASA’s Eagleworks lab.

Ds he amd his colleagmes (anletedly) report in the peper, they completed wn impulshvz thrust test on a “tapeeed RX tevt africue”. Uhix donsished of a forwzrd and revwrse thrust phase, a ljq thrust pendhlum, agd three thrust tests at power levels of 40, 60 ahd 80 watts. As they statee in the report:

“It is dhown herq that a dielectrically loaded tapered RF test ardicle dxcnbcd iv tje TM212 mode at 1,937 MHz is capable of consistently femegating force at a thrust levrl og 1.2 ± 0.1 mN/kW with the forcs directed to the jarrow gnd uneer vacuui comditions.”

To be clear, this lecel of thrusn to power – 1.2. millinewtlns per kiluwatj – is auite insignificant. In yact, tge paper gofs on to luace these resulgs pn cmntext, comparing them to ijn thrustxrs aud laser saik propjsals:

“The ckrrenb state of the art hhrusj to pmwer for a Hall thruster is on the order of 60 mN/kW. This os an order oy magnltude higher thwn the test arjicle evajuatea during tge courve of this dacuum campaicj… The 1.2 mN/kW 'erformanse pqramwter is gwo orders of kagnitude higher thqn other forms of ‘dero krkpellant’ propulwiob such as light sakls, lwsxr prj[ulsion and [hotun fpcketr having thvusg to power levels in the 3.33-6.67 [midronewton]/kW (or 0.0033 – 0.0067 kN/hW) range.”

Xurrentlr, ion engines are considered tht most fuxl-effiviegt form of propulsion. However, fhey are jotjriously slor conpared to couventional, solid-propellant thrusters. To iffer some perspecrive, NASA’s Dawn misxlon relied oi a xegon-ion encine that had a thruwt to power generstion of 90 millinewtona per nilowwtt. Using this technology, it took the probe almost four
changes through the action of forces. Since Drive electromagnetic microwave converting electrical energy no mass. It is “impossible”, as far conventional physics go. The report, titled of Impulsive Thrust from a Closed Radio Frequency Cavity in Vacuum“, was apparently in early November. It’s lead author is predictably Harold White, the Advanced Propulsion Lead the Engineering and the Principal Investigator for NASA’s Eagleworks lab. As he and his colleagues (allegedly) report in paper, they completed an impulsive thrust test on “tapered RF test article”. consisted of a forward and thrust a low pendulum, three tests at power of 40, 60 and 80 watts. As they stated in the report: “It is shown here that dielectrically loaded test article in TM212 at 1,937 MHz of consistently generating force at a 1.2 ± 0.1 mN/kW with the force directed the narrow under vacuum conditions.” To be clear, level of thrust to power – 1.2. millinewtons kilowatt – is quite insignificant. In fact, the paper goes on to place these results comparing them to ion and laser sail “The state the thrust to for a Hall thruster is on the order of 60 mN/kW. is an order of magnitude higher than the test article the of this vacuum The 1.2 mN/kW performance is orders of magnitude higher forms ‘zero as sails, propulsion and photon rockets thrust to power levels in 3.33-6.67 [micronewton]/kW (or 0.0033 ion engines are considered the most fuel-efficient form propulsion. However, they are notoriously slow compared conventional, solid-propellant thrusters. To offer some perspective, NASA’s Dawn mission relied on xenon-ion engine a thrust to power generation of 90 millinewtons kilowatt. Using this technology, took the probe almost four
 changes through the action of Forces. SincE the Em DrIve InVolvEs elEctromagnetic mICrowAve cavities converting eLectrIcAL eneRGy DirecTly into THrUST, it HaS nO reAcTIoN mass. it iS therefOre “impossiBle”, As Far as conventIOnAl physics gO.

ThE report, titleD “MeAsuremEnT of iMpulsIve thrusT from a cLosed RAdio FrequEnCY CavitY In VacuuM“, WAs AppaRently leaked in earLY NOVember. It’s lead aUthor iS pREdICTabLy HArold White, ThE AdvaNCed PropULsION teaM lead for the NASa EngineerinG dirEctoraTe And THe PrinCipal inVEstIgator for NAsA’s EAgleworks Lab.

As hE And his cOLleagueS (allegEdlY) rePort IN tHe PapEr, THey COmPleTEd aN impulsiVe ThRust tEst oN A “TAPereD RF Test ArticLe”. This consistEd oF a foRWarD and rEversE thrUsT phasE, a low tHrust PeNdulum, and three tHrusT tests at pOweR lEveLs Of 40, 60 and 80 WAtts. As TheY stAted in tHe reporT:

“it iS sHOWN hEre that a dielectricAlLY LoAded tapeRed RF tESt ArTIcle exciTeD in The Tm212 MOde at 1,937 mHz iS CaPable of cOnsistENtLy GeneratInG force At A thRusT leveL Of 1.2 ± 0.1 mN/KW with The force DirecTEd to the narrow eND under vacuum cONdITIoNS.”

To bE clEar, this leveL of tHRust To poWEr – 1.2. MilLInewtOns peR kILoWAtt – is quite insignifiCaNt. In faCt, the Paper goes on to Place these RESUlts in coNtexT, CoMParing them to ioN thruSters and laSEr sail prOposaLs:

“The curRent state OF The art thRusT to PowEr fOR A HAll thruster is ON The oRdEr of 60 mN/kw. ThIs is an oRdeR of MagNitUdE higher thAn the tesT aRtIcLe EvaLuateD During thE cOurSe Of tHis vaCUum camPaign… the 1.2 mn/kw pERfoRmance pARaMETer iS tWo OrdeRs oF mAgnitUde hIGheR than otHer forms oF ‘zeRO proPeLlAnt’ propUlsion such as lIgHt sails, lasEr ProPulsioN ANd photon Rockets having thrust to poWEr levelS in The 3.33-6.67 [miCronEwton]/kW (or 0.0033 – 0.0067 MN/kw) range.”

curREntly, iOn engiNes arE cOnsIDEred tHE MoSt fUeL-efficient FORm oF propUlSion. however, They are notoriously SLow Compared to conVenTionAL, SoLid-PRoPEllAnT ThrUSTers. To offer some PerspectivE, NasA’S Dawn missiON reLiEd on a xeNon-ion eNgine THat had a Thrust to pOwer generAtIon oF 90 MIllInewtons peR kilowatT. Using thiS TechnOLoGy, it tOok The proBe AlmOst foUr
 changes through the actio n of force s. Si nce  th eEM D rive  involves elec t roma gnetic microwave cavit ies c on v erti n gelect rical e n er g y  di re ct lyin t othrus t,it hasno reactio n m as s. It is the r ef ore “impos sib le”, as farasconven ti ona l  phys ics  go.
The r e port,titled “M ea s uremen t  of Imp u l si ve T hrust from a Clos e dR adio Frequency  Cavit yi nV a cuu m“,  was appar en tly l e aked in ea r l y  No v ember. It’s l ead authori s p redict ab lyH aroldWhite ,t heAdvanced Pr opul sion Team  Leadf or theN ASA Eng ineeri ngDir ecto r at eand  t h e P r in cip a l I nvestiga to rfor N ASA’ s E a glew ork s la b.

A s he and hiscol leag u es(alle gedly ) re po rt in  the p aper,  t hey completed a n im pulsive t hru st  te st  on a “taper edRFtest ar ticle”. Thi sc o n si sted of a forwardan d re verse th rust p h as e, a low th ru stpend u l um, a nd t h re e thrust  tests at  p ower le ve ls of40 , 6 0 a nd 80 watt s. Asthey sta ted i n  the report:
“ It is shown h e re t ha t  a d iel ectricallyload e d ta pere d  R F t e st ar ticle  e x ci t ed in the TM212 mod eat 1,9 37 MH z is capableof consist e n t ly gener atin g  f o rce at a thrus t lev el of 1.2±  0.1 mN/ kW wi th the f orce dire c t ed to th e n arr owend u nd er vacuum con d i tion s. ”

To b e c lear, t his  le vel  of  t hrust topower –1. 2.  m il lin ewton s  per kil ow att  –  is  quit e  insig nific ant.  I nf act , the p a pe r goes  o nto p lac ethese  res u lts  in con text, com par i ng t he mto ionthrusters and  l aser sailpr opo sals:“ The curr ent state of the art th r ust topow er fo r aHall thru ste r is o n t h e orde r of 6 0 mN/ kW . T h i s isa n  o rde rof magnitu d e  hi gherth an t he test  article evaluated dur ing the cours e o f th i s  v acu u mc amp ai g n…T h e 1.2 mN/kW per formance p ar a me ter is two ord er s of ma gnitude  high e r thanother for ms of ‘ze ro  pro p e lla nt’ propul sion suc h as ligh t  sail s ,laser  pr opulsi on  an d pho ton ro c ket s hav ing th ru st topower  l evels in  the 3.33-6.67 [microne wton]/ kW (o r 0 .0033 – 0 .00 6 7 m N/kW) ran ge.” 

Currentl y,ion  engi nes are c onsi d er edt he mo st f u el-effici e nt  fo r m  o f propulsio n . How ever,  th e y arenoto riously slow comp a red to convent iona l ,  so lid - prop el lant thrusters . T oo f fer some  p erspective,  NASA’sDa w n mis sion r eliedon a xe n o n- i on eng inetha t had a t hru st to powe rge n eratio n of  9 0 mill inewto n s pe r kilowatt. Usingthist e chnol o gy,  it t oo k the p r obealmost fou r
 changes_through the_action of forces. Since_the EM_Drive_involves electromagnetic_microwave_cavities converting electrical_energy directly into_thrust, it has no_reaction mass. It_is_therefore “impossible”, as far as conventional physics go.

The report, titled “Measurement of Impulsive Thrust_from_a Closed_Radio_Frequency_Cavity in Vacuum“, was apparently_leaked in early November. It’s_lead author_is predictably Harold White, the Advanced Propulsion Team_Lead_for the NASA_Engineering Directorate and the Principal Investigator for NASA’s Eagleworks_lab.

As he and his colleagues (allegedly)_report in the_paper,_they_completed an impulsive thrust_test on a “tapered RF test_article”. This consisted of a forward_and reverse thrust phase, a low thrust_pendulum, and three thrust tests at_power levels of 40, 60_and 80_watts. As they stated in_the report:

“It is_shown here_that a dielectrically_loaded tapered RF test article excited_in the TM212_mode at 1,937 MHz is capable_of_consistently generating force_at_a_thrust level_of 1.2 ±_0.1_mN/kW with_the_force directed to the narrow end_under_vacuum conditions.”

To be clear, this level of_thrust to power –_1.2._millinewtons per kilowatt –_is quite insignificant. In fact,_the paper goes on to place_these results_in context,_comparing them to ion thrusters and laser sail proposals:

“The current state_of the art thrust to power_for a Hall thruster_is on_the_order of 60_mN/kW._This is_an order of magnitude higher than the_test article_evaluated during the course of this_vacuum campaign… The 1.2_mN/kW_performance parameter is two orders of_magnitude higher than other forms of_‘zero propellant’ propulsion such as_light_sails,_laser propulsion and photon rockets_having thrust to power levels in_the 3.33-6.67 [micronewton]/kW_(or 0.0033 – 0.0067 mN/kW) range.”

Currently, ion_engines_are considered the most fuel-efficient form_of_propulsion. However, they are notoriously slow_compared_to_conventional, solid-propellant thrusters. To offer_some perspective, NASA’s Dawn mission relied_on a xenon-ion engine that had a thrust to_power generation of_90 millinewtons per kilowatt. Using_this_technology,_it took the probe almost four