jbeazley wrote:

The recent posts on radiator installations reminded me of an old
question.

Does anyone have any information wing or shoulder radiator installations
similar to that done for the DeHavilland Mosquito.

I'm curious how effective they were and how much they would
affect any laminar flow on modern wings?

Cary

Unfortunately I don't have any data right at the moment but I will
scan some from Hoerner Fluid Dynamic Drag. (Good book to buy used.)

Also check NASA  T reports 743 1942
"""""""""""""""  L report L-407 1943
'''''''''''''''  T Note 3126 1954

I am sure it would screw up the flow aft of the outlet somewhat.
I could not have been too bad as the DeHavilland Mosquito was very
fast.

Here also is a picture of the combined rad outlet and wing
flap on an Me109. The Me109 also had a rad partially buried in the wing.

Paul Lamar

Here is where to get the reports in .pdf file format.
http://naca.larc.nasa.gov/

This is a screen capture from the pdf file on one  of the configurations
from NACA T743 1942. Note that it works better as the angle of attack
increases. A good thing as we climb at high angles of attack.
The down side to this report is it does not incorporate modern
thin core and bell shaped duct thinking as outlined by 
Kuchemann & Weber and Kays & London. That came ten years later.

Another problem with this is fitting it into the wing
while still getting the air past the spar web.

Basically someone needs to start over on this sort of thing.
Not likely to happen unless NASA quits shooting off $500 million
each month on the silly space shuttle and gets down to solving practical
problems like liquid cooled general aviation internal combustion
engines.

Paul Lamar
 
The AirCraft Rotary Engine NewsLetter.              Powered by Linux.
ACRE NL web site.
http://home.earthlink.net/~rotaryeng/            http://www.linux.org