Recent content by Jugman

Actually its the other way around. P&W and Wright designed their engines for military use then adapted them for commercial use. A major reason radials had better reliability is they had somewhat lower BMEP. For example the BMEP for the R-2800-21 at takeoff and rated power were 95% and 92%...

@Shortround6 The A-20's belly tank was a drop tank and it could be used with bombs in the bomb bay. It weighed 350lb and the filler neck limited glide angle* for bombs in the front bomb bay somewhat. A late model A-20G-35-DO, at an overload take-off weight of 27,000lb with four M64 in the...

The V-1710-89/91 should add around 1,400 to 2,00lbs. Even for single-engine fighters the drag advantage of liquid-cooled engines is not that significant. For large multi-engine aircraft even less so. A type B could be used but critical altitude would be reduced. Above ~25,000ft power would...

V-1710-91/R-1820/R-2600B TO/ mil power 1425, 1200, 1700 Normal rated 1100, 1000, 1500 Max lean cruise 795, 750, 1125 Above 23'000ft or so the B-17 had to cruise in auto-rich in order to produce enough power to maintain a suboptimal cruise profile. The V-1710 doesn't offer enough improvement to...

Bodie is the only author that I can recall that makes the claim that the R-2600 was unsuitable for turbos. The only two turbo R-2600 installations that I know of are the A-20 and the F6F-2. The Turbo A-20 was just a really dumb idea for a tactical bomber that primary mission is dropping 20lb...

Just removing the guns will not give you enough of a speed boost to make difference. The only engine that gives enough power that probably will fit is the R-2600. There will be a 3,000lb to 4,000lb weight penalty, but a R-2600 powered B-17 will be able to climb to, and cruise at high altitudes...

WW2 carburetors were self metering or compensating carburetors , so there was no intermediate throttle. Even with the intermediate throttle I would hardly call the system "very complex". At least no more complex than the automatic gear change or boost regulator of the two-stage Merlin.

Per "Curtiss-Wright Engine Specs, 1930 - 1983" Wright built three models of two-stage R-2600. -10 9 built -14 1 built A BB series model and optional engine for the F7F -16 2 built Improved -10, may be the actual engine used in the XF6F-1 All three have the same ratios; 7:1 main stage and...

Anti-Detonation Injection. Aka water injection.

Another factor, as far as fighters are concerned, is roll mass and inertia. If you had a DH Hornet with two-stage Griffons it would weigh at least 1500lbs more and this weight is concentrated some 8ft or so away from the center. The USAAF considered the 600lb weight penalty ADI would add to the...

The P-47 had a built-in air filter. Many other aircraft ( P-38, P-51, P-61 to name three) did as well.

In short, no it wasn't rubbish. https://youtu.be/PV_65rLWRa8?si=YKvawYk2ygQ8FOYu https://youtu.be/9C1Zo1zKkAw?si=yon-1mtDS_p63S9n

https://youtu.be/8XYO-mj1ugg?si=t9buTs6QcfphnDfV It's seems more likely to be double engine failure.

And what source do you have to support a maximum speed of 380mph? In light of the fact that the XP-39 could not develop full power do to excessive vibration and that the 12-13" diameter temporary oil-cooler installation produced excessive drag, even 340 mph seems improbable. The time-line of...

i was looking at the TOCL chart from T.O. No. 01-5EC-1 15-Sept-1942. It says 1782ft for the ground run and 2550ft to clear 50 feet. There's a good chance that the chart is en error.