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Celera 500L (and high altitude discussion)


The specs they are quoting are unbelievable, for a piston engine.

The patent goes on to describe a notional aircraft that would cruise between 460 and 510 miles per hour at an altitude of up to 65,000 feet, yielding a fuel efficiency rate of between 30 and 42 miles per gallon. To put this in perspective, the Pilatus PC-12, a popular light, single-engine turboprop aircraft has a service ceiling of 30,000 feet, a cruising speed just under 330 miles per hour, and still burns, on average, 66 gallons of jet fuel per hour, for a fuel economy of roughly five miles to the gallon. Even going to a Learjet 70, which has similar speed performance to what’s stated in the Celera patent documents, but still nowhere near as high a ceiling, we are talking about roughly three miles per gallon of gas at cruise. So, Otto Aviation is talking about performance that is at least 10 times more efficient than existing light business jets with similar cruise capabilities.

Shoreham EGKA, United Kingdom

Reminds me of the Raptor which I am following the development of: Although it’s a canard design the designer also has lofty goals for efficiency, but not quite as ostentatious as The Celery. Maybe there is something in the bullet profile though.

LKTB->EGBJ, United Kingdom

Oh man, an extra 400 got pregnant after an affair with a kc135…
Seems a lot of vapor to me.

LFMD, France

“Celera” (spelled “Celerat” but the final “t” is silent) means “crook” in French.


It follows the current trend in aero design. Laminar flow as much as possible, keep propeller behind to not disturb it, and boundary layer ingestion engine.
They can achieve a good percentage of drag reduction, but anyway the specs seems way too optimistic.

LECU - Madrid, Spain

Is the claimed ceiling actually impossible?

Interesting numbers here. One record was set in 1938 by a biplane, at 56000ft. A UAV has done 67000ft so propellers clearly do work up there. The manned record is 60000ft.

Also, if you have 2 engines driving one prop, is the Vs still limited to 60kt?

means “crook” in French

Clearly they forgot to do the obligatory “focus group” on product naming

Shoreham EGKA, United Kingdom

PC12 lands in 600m runway, it needs drag to do that

A bullet design with prop in the back maybe best for cruise but will have a huge pitch/speed/power stability
How do you slow down? flare to land? recover from a stall?

My bet it could deliver 460mph at 500hp but stall speeds could be in the 120kts, type rating includes 20h on A10…

Last Edited by Ibra at 20 Jun 14:30
ESSEX, United Kingdom

Peter wrote:

if you have 2 engines driving one prop, is the Vs still limited to 60kt

No idea. But irrelevant here, since it has one engine – according to the FAA aircraft registry

Biggin Hill

Peter wrote:

Is the claimed ceiling actually impossible?
At 65,000ft the atmospheric pressure is down to 0.06 atm. You need to move a lot of volume to produce any amount of power (for which you need mass). The turbo-compressor system will have to be tuned in a very particular way and work quite hard, because pistons going up and down are mostly useless up there.
The prop is again too small to displace enough volume and produce any thrust at high altitude.
The mock-up has far too little wing surface to carry this big suppository of a fuselage up to that thin atmosphere.
And let’s not talk about structural strength (and implied weight) needed for the pressurization.

All these, and more, trade-offs are in the U-2 design, and that thing does not look like a U-2.

Investor scam.

ESMK, Sweden

The Grob Strato 2C went up a little further, 78000ft

Aufwind GmbH
EKPB, Germany
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