"Eunometic" <***@yahoo.com.au> wrote in message news:fdf2d825-f044-45d2-93d2-***@i20g2000prf.googlegroups.com...
On Nov 22, 11:06 am, webpa <***@aol.com> wrote:
(snip)
Post by EunometicPost by webpaWe should remember that the P-51H was re-designed as a light-weight
interceptor. IIRC: Thinner skins in many places; bigger holes in
webs, deleted armour, lighter-weight hydraulic accumulator tanks, and
the latest-greatest Merlin. Built (IIRC) only at Ft Worth.
1 Lengthened tail
2 Enlarged Height Vertical Fin)
(The P-51D had some serious lateral stabillity issues which lead to
greater than usual problems in spin recovery and possible breakup
during snap rolls, hence the increased tail moment arm and tail area)
The D model lost some of its stability thanks to the loss of rear fuselage
area when the bubble canopy was introduced, hence the tail fillet
modification. This was aggravated by the amount of fuel in the rear
fuselage tank. "Serious lateral stability issues" is an exaggeration.
Post by Eunometic3 Strengthened tail.
(So the P-51H was strengthened where it was important and 'lightened'
where it wasn't.)
4 New wing cross section. IE it had a new, thinner wing.
5 New, larger canopy
6 Tail fuel tank was deleted (I assume the improved aerodynamics
would have just about made up for the loss of the troublesome tail tank)
Try the internal fuel tanks were rearranged, to give 255 US gallons of
fuel, versus the 269 gallons of the P-51D. The more powerful engine
seems to have meant the range on internal fuel dropped from 950 to
850 miles compared with the D model. The H cruised about 20
mph faster.
Post by EunometicI don't think the P-51H was 'weak' and it would be interesting to find
out what load factors the P-51D was designed for.
To quote Dean in America's hundred thousand the P-51A was stressed
for an allowable flight load limit of 8 G and break up at 12 G.
Post by EunometicUS fighters were stressed to 9G in the assumption that they would be
doing extreme maneuvers in the dense lower atmosphere as part of
support of ground attack aircraft while RAF aircraft like the spitfire
were stressed to a 6G standard since they emphasised other
factors such as climb and turn.
To quote the RAF contract for a 1930 fighter design,
"The strength of the main structure when carrying the load specified in
paragraph 3, plus 100 pounds, shall not be less than as specified
hereunder
- Load factor throughout the structure with the centre of pressure in
its most forward position 9.0
-Load factor for wing structure with the center of pressure in its
most backward position 6.0
- Load factor in terminal nose dive 1.75."
So where do the RAF 6 and USAAF 9 G figures come from?
Geoffrey Sinclair
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