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I was aware of that from the very beginning Bill and a long time before that as-well.
Oh btw, Gene notes that the full elliptical lift distribution occuring in turns wasn't a design feature from the start, which I said it was, so on that point I was wrong and I gladly admit it.
Quote:
Originally Posted by Soren
I see, so I was wrong when I said that Fw-190's wing achieved basically fully elliptical lift distribution in turns ?
No you are right. That is what causes the harsh stall. It is not a design feature however. It is just and explanation for the two different stall characteristics of the design.
Quote:
Originally Posted by Soren
It was my understanding that the Spitfire's wing didn't achieve fully elliptical lift distribution because of the washout applied to the wing all the way out to the tips.
You are right on this too. The Spitfire does not achieve the full efficiency benefits of elliptical wing construction due to the washout. At the same time though it is probably the most efficient of the three. If we examine the aircraft at a design optimum point, you will find little to no difference.
So the debate is now settled I hope.
Since the Mustang and FW190 are designed to most efficient at one design point and the Spitfire has an elliptical wing which is efficient at all points, Lednicer's observation is correct in that the Spitfire probably has the most optimal of the three. Probably is used because the aerodynamic twist in the Spitfire wings in order to prevent the wing from stalling all at once reduces this efficiency. That too would be designed for an optimal point of performance.
Soren I think you need to be specific on which part Bill was wrong about.
And Bill, Soren already admitted that he was wrong about the aeroelastic effects being an intentional design feature, though they did occur in the way he described.
KK - you might go back to page 77 when I outlined the foundation of elliptical wing design, how trapezoidal designs could closely approximate elliptical load distribution through twist and tip chord, then finally how 'G' forces did not influence lift distribution Until aeroelastic deformation (torsion/twist- or bending).
See when Soren started 'seeing the light'
And mentioned earlier was that the 23000 series airfoil itself (without washout) generated an elliptical lift distribution, without an elliptical (or elliptical-like) planform
ALL basic wings can be made to demonstrate an 'elliptical like' lift distribution - An Elliptical planform wing for example, using that airfoil, would get an elliptical lift distribution along the entire span with no change in chord twist as you move span wise from root to tip.
A Trapezoidal wing (i.e P-51 or Fw 190) using that same airfoil has to have twist of the chord as you move spanwise from root to tip. It will not be as efficient relative to total induced drag of the SAME airfoil as the Elliptical wing plan form. However, as you get a tip chord to root chord ratio around .4 to .5 you are getting close.
The reason the Elliptical Wing planform of the Spit used twist was to ensure that the inboard region of the wing would start to reach CLmax before the tip area. (the twist is 'downward' reducing the local angle of attack as you move spanwise outboard) - more at the tip than the root.So, the twist reduced the efficiency of the Elliptical planform with respect to induced drag (slightly) but gained additional tip stall prevention
And one final thing, though the stalling occurring in high G turns is a disadvantage, the elliptical lift (and thus low induced drag) would benefit turn performance.
OK, Bill but what part do you still disagree with Soren about?
Not that it matters, but wasnt something like 80% of the LW grounded or otherwise non-operational at the end of the war, mostly due to fuel shortages, but also because of pilot deficiencies. Dont the figures for the K-4 therfore appear to be somewhat misleading from that stanpoint. Perhaps not relevant to this thread, I admit
Its also worth remembering that not all aircraft assigned to an RAF fighter squadron flew operational sorties; British practice was to use 20-22 plane strenght squadron establishments, of which however a maximum of 12 planes would fly operational sorties;
Actual production of the Mk XIV Spitfire was 957, not 482. Not sure what your sources are for those figures, but they are a bit low.
By ponsford:
Alfred Price cites April 45 figures of Luftwaffe serviceability showing JG 26 and 27 could muster a little over 100 Fw 190s and Bf109s between them, which was less than either the Spitfire XIVs or Tempests facing them in NW Germany.
Soren misquoted his original comments that started this long running debate to Gene - he pulled out the original context 'of designing elliptical distribution' for a high G turn and inserted mine regarding 'aeroelastic effects combined with the tip design' were the causes of the stall.
Total Delivered by end of month - Number delivered that month
1943 : 18 18
01-44 : 30 12
02-44 : 45 15
03-44 : 50 05
04-44 : 56 06
05-44 : 68 12
06-44 : 101 33
07-44 : 129 28
08-44 : 151 22
09-44 : 185 34
10-44 : 245 60
11-44 : 300 55
12-44 : 341 41
01-45 : 399 58
02-45 : 511 112
03-45 : 648 137
04-45 : 743 95
05-45 : 815 72
06-45 : 844 29
07-45 : 873 29
08-45 : 891 18
09-45 : 898 7
10-45 : 904 6
11-45 : 911 7
The problem is that a lot more was facing the 2nd TAF than just JG 26 and JG 27. There were a lot more other units on the West, not to mention that in April 1945, there was hardly a seperate 'Western' and 'Eastern' front. The Reich itself was the battleground.
I believe what you recall seeing was just the newest of Mike Williams`s brainchilds - he tries to exclude half a dozen LW unit from the unit strenght count, claiming that they weren`t in North-West Germany, but say, 100km further south or east - waving a strenght lists which shows the Luftlotte Reich only he pulled off from Holm`s site and arriving at his usual dubious conclusions.
Apart from that, I seriously doubt the RAF could muster more then 100 Tempests and Mk XIV Spitfires for operational sorties at all, there were simply not enough in Squadrons for more, and the reason for that was that they simply could not produce more, for whatever reason.