And on the P-39 the coolant radiator was put in the leading edges of both wings?
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And on the P-39 the coolant radiator was put in the leading edges of both wings?Coolant radiator was in left (facing forward) wing leading edge. Did not have an adjustable outlet.
No, I get that in the way it was installed below the engine: However, if like on the P-63, the oil tank was moved forward and the turbo was placed behind the engine instead of under it, would such a design have been workable?Like I have said before, that turbo installation in the P-39 would have made Rube Goldberg proud.
All they really needed to make the early P-39s(D,F,K and L) high altitude planes (in 1942) was less weight.
The oil tank wasn't moved on the P-63, it was the coolant tank that was moved up between the pilot and engine that made room for the mechanical second stage supercharger (not a turbo). There was enough room there for the mechanical second stage but not a turbo which required more space. Plus all the internal ducting (exhaust to turbo to intercooler to carburetor) and the intercooler itself, none of which was used/needed on the P-63. Adding the turbo where the oil tank was would have caused a CG problem also. Workable is the key word, and that would have been difficult without substantially enlarging the P-39/63. The P-47 used this arrangement (turbo in the rear fuselage) and was a much larger plane than the P-39/63. Much easier/quicker to use the mechanical second stage rather than the turbo. Just my opinion.No, I get that in the way it was installed below the engine: However, if like on the P-63, the oil tank was moved forward and the turbo was placed behind the engine instead of under it, would such a design have been workable?
Also, would there have been enough room to mount the intercooler as placed?
Obviously the higher supercharger gear ratio (9.6 vs 8.8) in the P-39M/N/Q provided about 100 extra HP and better performance but the earlier D,F,K and L with the 8.8 engines would have benefited greatly from an easy weight reduction program.And a better high altitude supercharger for the engine.
Sorry about that...P-39 Expert said:The oil tank wasn't moved on the P-63, it was the coolant tank that was moved up between the pilot and engine that made room for the mechanical second stage supercharger (not a turbo).
The P-63 was originally planned around having an intercooler (not sure where), but ultimately they went with anti-detonant...There was enough room there for the mechanical second stage but not a turbo which required more space. Plus all the internal ducting (exhaust to turbo to intercooler to carburetor) and the intercooler itself, none of which was used/needed on the P-63.
So the turbocharger weighed more than the supercharger, as well as all it's ducting and the intercooler?Adding the turbo where the oil tank was would have caused a CG problem also.
Would lengthening the P-39 to the P-63's length have provided any fix? If not, would an arrangement similar to the YP-37 and YB-38 work (also below the engine but better flow)Workable is the key word, and that would have been difficult without substantially enlarging the P-39/63.
I agree, it's just kind of an intellectual exercise -- see what would/would not work. That, and I don't think Allison had a 2nd stage developed at the time (that said, it could be bolted on without difficulty due to the design).Much easier/quicker to use the mechanical second stage rather than the turbo.
The removal of the 4 x 7.62's seems like a good idea to be honest, I never really understood why they put them in the design: I figure that 2 x 0.50 in the wing, 2 x 0.50 in the nose, and 1 x 37mm would be quite good. As for the nose armor plate, and small panels around the rear-armor glass, do you mean the bulletproof glass or firewall & that metal thing protecting the pilot's head?Simply remove the (useless) four .30 caliber light machine guns from the wings, the nose armor plate (100#) and the small armor panels in the cockpit turnover bulkhead around the rear armor glass but leave all the rest of the armor plate/glass protecting the pilot and oil tank.
The turbo and the mechanical second stage (MSS) probably weighed about the same but if the turbo went where the oil tank was it would be further aft of the CG than the MSS causing (more) balance issues. The ducting issue was mainly internal space not weight.Sorry about that...
The P-63 was originally planned around having an intercooler (not sure where), but ultimately they went with anti-detonant...
So the turbocharger weighed more than the supercharger, as well as all it's ducting and the intercooler?
Would lengthening the P-39 to the P-63's length have provided any fix? If not, would an arrangement similar to the YP-37 and YB-38 work (also below the engine but better flow)
I agree, it's just kind of an intellectual exercise -- see what would/would not work. That, and I don't think Allison had a 2nd stage developed at the time (that said, it could be bolted on without difficulty due to the design).
The removal of the 4 x 7.62's seems like a good idea to be honest, I never really understood why they put them in the design: I figure that 2 x 0.50 in the wing, 2 x 0.50 in the nose, and 1 x 37mm would be quite good. As for the nose armor plate, and small panels around the rear-armor glass, do you mean the bulletproof glass or firewall & that metal thing protecting the pilot's head?
The P-63 was originally planned around having an intercooler (not sure where), but ultimately they went with anti-detonant...
Those 4x.30cal wing guns ruined the P-39. Without them the plane was lighter and the space vacated by the guns could have been used for more fuel if desired. Main problem was they weren't powerful enough to be effective as the British proved in the Battle of Britain. No other AAF production fighter used them. We can blame our friends the British for the .30 caliber wing guns, they specified them on the export P-400.
OkayThe turbo and the mechanical second stage (MSS) probably weighed about the same but if the turbo went where the oil tank was it would be further aft of the CG than the MSS causing (more) balance issues. The ducting issue was mainly internal space not weight.
Stability usually implies a relationship in control surface effectiveness as well as mass...The P-63 was lengthened but it was all in the tail cone, not in the engine compartment. . . . Lengthening was for stability, not internal space for the MSS.
Those 4x.30cal wing guns ruined the P-39. Without them the plane was lighter and the space vacated by the guns could have been used for more fuel if desired.
It is, isn't it?P-39 was just too small for a turbo, intercooler and all the internal ducting IMO. Fun to talk about though.
And the reason for this delay had to do with the fact thatAllison MSS was in production in March 1943, just for time reference.
I'm not sure the pilots would've liked that!Regarding the armor plate, keep the rear armor glass and delete the small pieces of armor on the turnover bulkhead (that metal thing protecting the pilot's head).
Makes a lot of sense, there was additional room in the P-63 radiator area for an intercooler if necessary. I like the way Bell got around the intercooler too.It was a liquid to air intercooler, very much like the one on the Merlin, positioned above the engine stage supercharger. This require relocating the carburetor to the intake of the auxiliary supercharger.
The radiator for the intercooler was, presumably, located with or near the engine radiator.
I'm not sure how this would have worked, but I know this configuration was pretty similar and worked on the XB-38...
View attachment 492104
... the problem with the P-37 was the configuration of the radiators producing an excessively long nose.
And the reason for this delay had to do with the fact that
Oh, okayIt was a liquid to air intercooler, very much like the one on the Merlin, positioned above the engine stage supercharger. This require relocating the carburetor to the intake of the auxiliary supercharger.
They couldn't fit 1 x 0.50 in each wing?Not sure if the 0.50" mgs could have fitted in the P-39's wings, but if they couldn't it would explain why the 2 x 0.30" mgs in each wing were chosen.
While a little beyond the scope of the P-39 discussion, if the YP-37 had the following repositioned in the following waysThe XB-38 used the standard B-17 turbo location, had a chin mounted intercooler and leading edge radiators (between the nacelles).
The 4 x .30caliber wing guns weighed around 377# with 1000rpg (just guns & ammo, not including mounts, chargers, heaters and ammo boxes). Pull all that out and you are looking at 400# weight saved. Later models loaded the .30s with 300rpg to save weight. This reduced the weight of the four guns and ammo to approximately 200# total. So the amount you save depends on the model, either 400# or 200# depending on load.Okay
Stability usually implies a relationship in control surface effectiveness as well as mass...
It is, isn't it?
- How much weight could be trimmed off by removing the 4 x 0.30" and all their ammo?
- How much fuel could be put in that volume
- Would 2 x 0.50 with normal rpg levels add any significant weight?
I'm not sure how this would have worked, but I know this configuration was pretty similar and worked on the XB-38...
View attachment 492104
... the problem with the P-37 was the configuration of the radiators producing an excessively long nose.
And the reason for this delay had to do with the fact that
I'm not sure the pilots would've liked that!
- There was little demand for inline engines in the United States
- The airlines had little interest as air-cooled engines were more reliable; the NACA cowl greatly improved cooling, and reduced drag
- Raceplane designers seemed to vary: The land-based guys used radials almost exclusively because the engines were lighter for the same power, and used very well designed cowlings, and built their planes as light as possible; the seaplane designers usually used liquid cooled or even surface-evaporative cooling and used the struts and braces as radiator surfaces.
- The USN had little interest in inline engines after the late 1920's or early 1930's: Radials were more compact and more reliable, though they were willing, at times, to evaluate inlines if they provided a marked improvement in performance, and as a result funded the Lycoming H-2470, Pratt & Whitney X-1800/H-2240/2600, H-3130/3730
- The USAAC really was the only organization that wanted inline engines, and to this effect, they funded the Continental O-1230/I-1430 Hyper-engine, the V-1710, X-3420/V-3420, and the Lycoming O-1230
- The massive funding of a large number of inline-engines: Including the Continental O-1230/I-1430, Lycoming O-1230, H-2470, Pratt & Whitney X-1800/H-2240/2600, H-3130/3730, and the Allison V-1710, X-3420/V-3420 meant that essentially 7 designs were being developed (some of them were reconfigurations and resizing) with little commercial demand in a depression; the result was a massive breadth but little depth to it all.
- The USAAC mostly favored turbochargers over superchargers
- They were sometimes willing to look into two-stage superchargers: The problem was not that they looked into turbochargers (the USN did that too at times), it's that they put turbochargers so far ahead in the running, that secondary stage superchargers were basically in the background not a close or moderate second
- The USN did look into the idea of twin-stage supercharging and made it work with the F4F-3, F4U-1 making their first flights in 1940.
Weight of two .50cal MGs and 300rpg weighed 330# on the P-39Q, but those were hung underneath the wing.
No.With the wing guns suspended beneath, and not inside, the wing, was any extra fuel carried in the wing of the P-39Q?