Can anyone pinpoint the amount of drag that is reduced by the all moving ruddervator vs traditional with stabiliser and rudder + elevator system ?
I get the feeling it could be 4-5% of the total drag ?
Daniel Raymer placed engines apart and also lost the vertical stabilisers in 1981 entry !
http://www.youtube.com/watch?v=4QxUexu-KAQ
Cool; 
Measures; http://sobchak.files.wordpress.com/2008/12/rockjpg.jpg
Can be found here as well; http://www.aircraftdesign.com/atf_rockwell_d703-11_raymer_hires.jpg
Seems that Daniel is/was fixed on this v-tail..here lite weight super cruise fighter; http://www.aircraftdesign.com/dr3.jpg
…and here; http://www.aircraftdesign.com/ngaf.jpg
4 Sparrow and 2 Sidewinders consealed; http://www.aircraftdesign.com/atf3.jpg
http://maanpuolustus.net/attachments/boe1985preatf-jpg.1755/
topspeed, the drawings on Wikipedia aren’t entirely accurate. My frontal profiles are directly from the PAK FA patent and Lockheed Martin, so they’re as accurate as you can get. Also, I assumed 13.95 meter wingspan for the T-50, and 13.56 meter wingspan for the F-22.
As for the T-50 empty weight, Piotr Butowski cites 18,000 kg, though this may have increased slightly due to some of the structural reinforcements we saw after 2012.
I agree…the wiki 3-views are distorted badly.
Looks like the Honeywell F125-IN is more efficient than the F119 ? …..ie F-22 looses thrust in rerouting it ( air ) to the engine ?
I’d say F-22 is 3.4 times bigger than G1 would be ?! Rudder area ratio is spectacular 4.54 !
[ATTACH=CONFIG]227844[/ATTACH]
These look pretty accurate..are the elevator frontal areas added as well ?
Is the side view suppose to be total area ?
Now only one 🙂
Empty weight PAK FA 15500 kg – 17000 kg[ATTACH=CONFIG]227845[/ATTACH]
Have you subtracted the air intake holes from the frontal area ?
Paralay…..what did you just post…..two hotlinks to where ?
What say Rpr now ?
I increased the fuselage volume and added wash out ( aerodynamical twist ) to the wings.
If PAKFA and Chengdu manage to get more powerfull engines they can reach the G1/Raptor level !
:angel:
This new knowledge gives me a change to increase the frontal area in G1 to 2.61 m2 to be even with F-22 in frontal/power ratio ( which is still the best of all fighters ).
The wiki frontal alone gives 8.96 m2 but has considerably shorter rudders ( and thicker ) for F-22 than the side view indicates ( even 150 mm ).
Is the wikipedia span 13560 mm correct for the F-22 ?
Once more…I superimposed the wiki image under the colored image here in the right scale…and able to correct the way too thin rudders..and get the right area. I also saw that the PAKFA was 0.0025 % too small…and after correction I got the right size for it too.
Here the span and lenght are adjusted..it needed 3% more lenght to match with the “official” wing span.
So the wiki pic is distorted somehow ( and the frontal with 9.34 m2 cannot be right ).
To confuse everyone I also added the enlarged ( to meet the lenght based estimate ) wiki 3-view front with this image here and voila….we can see several new aspects.
There is a fair change that the PAKFA indeed is the same size with F-22 !?
What annoys me the most is that the length and span are not what are informed in the “official” 3-views in wiki.
This image gives 9.34 m2 when imported to Draft Sight ( Dassault Systemes ).
How do you figure the frontal area? The T-50 must have the largest wing area right?
I just count it from the image with a computer program.
Here is the 3-view with 100% exact F-22 measures ( in relation to others ) and a composed one from wikipedia .
This new wiki picture when scaled to right size gives frontal of 9.34 m2 for F-22 ???
Will the twin cannon nozzle fumes damage the engine if placed as shown here ?