Follow along with the video below to see how to install our site as a web app on your home screen.
Note: This feature may not be available in some browsers.
Ad: This forum contains affiliate links to products on Amazon and eBay. More information in Terms and rules
Hello,
Given the heavy weight of the plane, I was wondering how the P-47 accelerated in level flight as compared to other fighters of the era (both Allied and Axis). Any ideas?
P-47 escort fighter pilots learned very quickly not to get too low in any fights with 109s or 190s.
Depended on the flight regime. It was heavy and climbed poorly (though that got better with later more powerful engines and different props, but still still not great).
The design was optimised for high altitude missions. At 30.000+ it was a hot ship and surprisingly, in fact very manoeuvrable despite it's size and weight. At that height it's acceleration was acceptable (still plenty of engine power and drag had gone down with altitude).
The lower you went the worse it got. Not only heavy but pretty draggy (it's design really predated the 190 like tight, aerodynamic cowling designs of later air cooled designs). Again the change to the paddle props (which really traded speed for more 'bite' for better climb ...basically) and more engine power helped, but at 15,000ft or less it was not the fastest thing around in any way (climb, speed, acceleration).
P-47 escort fighter pilots learned very quickly not to get too low in any fights with 109s or 190s.
So the answer to your questions is, like all the fighter aircraft of the time, depends on the flight regime. For example in the late '43 versions, at 30,000ft it would run rings around a 190A. But at 20.000ft (let alone 10.000ft) the balance swings the other way.
Most props are going to be within a few percent of 80% at sea level. At 20,000ft or so were the air is about 1/2 as dense prop size and design becomes more important.The tables at AHT assume that all props have the efficiency of 80% - that would tend to skew results? Also, there is no exhaust thrust taken into account.
Most props are going to be within a few percent of 80% at sea level. At 20,000ft or so were the air is about 1/2 as dense prop size and design becomes more important.
Exhaust thrust doesn't quite equal power, it varies in efficiency with the speed (and altitude) of the aircraft. At 250mph and at sea level it contributes quite a bit less than it does at 20,000ft and 325-375mph.
The only figures I have are for a Hurricane II with a Merlin XX engine. <snip>
Very few radial engines had exhaust stacks as well executed as a a V-12. Please also remember that exhaust thrust is dependent on exhaust mass ( fuel, air and water/alcohol) early aircraft without water/alcohol/over rich mixtures and the like have less mass than later engines (or even two stage engines) , exhaust speed and to turn into useful power , the aircraft speed. the closer the match of the exhaust speed to the aircraft speed the more useful the exhaust thrust becomes. One of the great advantages of the variable pitch prop. At low pitch (take-off) the prop may be trying to accelerate the air to around 1/2 the speed it would be if it was stuck in high pitch. (Spitfire I Rotol) prop had a bit over 23 degrees pitch at low pitch and about 58 degrees at high pitch.
There may be a some minor effect or change due to exhaust thrust or a change in ranking if the positions were close but it is not a big game changer at low altitudes and speeds.
I don't disagree with your points about the P-47 but this statement is simply not true. P-47 pilots confidently took on their Luftwaffe adversaries even on the deck. I have many combat reports which support this contention. Of the first five I looked at (at random out of a total of about 300) three describe low level combats.
(snippage)
Cheers
Steve