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167,000 lbs / 6.7lbs/gal = 25,000 gallons/10,000km = 2.5 gallons/km or 16.75 lbs/km does not seem too bad a fuel burn per km, not much better than a tank!
Now for a time breakdown. Say a slow cruising speed of 700km/hr 10,000km/700km/hr=167,000lbs or 25,000gal/(14.25 hr trip time*60(determine fuel use per minute))=203lbs/min or 30gal/min
Sounds reasonable
Originally posted by minkey53
So cruising at 600 km/hr for 10,000 kms works out at what, roughly 16 hours flying time?
30 gallons of fuel per minute X 16 hours, that's nearly 30,000 gallons of fuel.
As I said, NO WAY can the B2 hold 30,000 gallons of fuel in it's skinny wings.
Retired Air Force Colonel Donald Ware has passed on to me information from a three-star general he knows who revealed to him in July that "the new Lockheed-Martin space shuttle [National Space Plane] and the B-2 [Stealth bomber] both have electro-gravitic systems on board;" and that " this explains why our 21 Northrop B-2s cost about a billion dollars each." Thus, after taking off conventionally, the B-2 can switch to antigravity mode, and, I have heard, fly around the world without refueling.
Originally posted by JOINTHERESISTANCE
Legitimate website, confession of anti grav on the b-2.
The B-2, however, is a flying-wing (or flying-wing/lifting-body hybrid, if you prefer). Northrop built Flying Wing bombers in the late '40s. The YB-49 flown in 1947 (eight 4,000 lb thrust turbojets) and the photo-recon version YB-49A in flown in 1950 (six 5,000 lb thrust turbojets) both had a thrust to weight ratio of 0.15—even lower than the B-2's. So, the mysterious technology that lets the "seriously underpowered" B-2 fly supposedly in violation of "conventional aerodynamic means" is that it isn't a conventional airframe. It isn't underpowered for a flying-wing or lifting-body where the fuselage provides significant aerodynamic lift. There's no need (or real evidence) for any "enormous electrogravitic lift force" in the B-2.
For reasons not yet de-classified, the B-2 charges its leading edge to a very high electrical potential difference from its exhaust stream.
It has been suggested (by Jane's Defence) that it augments the B-2's low thrust main engines. It is also a well known phenomenon that an ionised gas (plasma) will scatter a radar beam far more effectively than a solid surface of any conceivable shape. This could be the purpose of the high voltage leading edge. Another possibility is that it is for the purpose of reducing drag, since the leading edge of the B-2 might then move through a partial vacuum of ionised air which may be ionised and repelled by the high voltage. In any case, it is however true that Northrop engineers conducted wind tunnel tests using high voltage on a testbed wing leading edge to reduce supersonic drag as far back as 1968. These tests were with a view to breaking up the airflow ahead of the wing using electrical forces in order to soften a sonic boom. How this applies (if indeed it does at all) to the B-2 after an interval of many years is uncertain.
Originally posted by ALLis0NE
reply to post by minkey53
All aircraft obtain electric charges while flying through air. That is why ALL aircraft are grounded (connected to Earth) before they try to refuel them. They don't want an arc to ignite the gas vapors.
Originally posted by JIMC5499
I'm not saying a word about the construction. Last I heard that information was still classified.
By 'wingbox' I assume you mean the fuel bladders in the fuselage?
Originally posted by C0bzz
Here's a picture I took of a Boeing 777-300ER.
i46.tinypic.com...
Them wings are far smaller than those on the B-2, yet they (and the wingbox) can hold 47,890 US gal (181,280 L).