kdub104 wrote:Engine frontal area dictates drag i.e. F-135. F-35 is not meant to be a high Mach jet but rather, good performance at high subsonic speeds and good fuel consumption for its design envelope (bomber). F-22 has engines with smaller frontal area and less overall drag and it has a much different design and mission.

Have been ignorant of this until now but the A-10 is a classic example of design and engine function to meet mission requirements.

I came across this site and if the author is correct, the F414 is the closest engine to a turbojet. The EJ200 is perhaps the best engine pound and inch per pound and inch into today's modern world of engines.

https://defenseissues.net/2014/12/06/fi ... mparision/The F-119 is simply out of this world but only due to its overall larger size. Based on this link, it appears the F404 is actually quite a poor engine.

Inlet diameter is a poor method for determining frontal area, as the maximum diameter of the engine is usually larger than the inlet, and it is the maximum diameter of the engine that determines the frontal area constraints of the engine installation.

Aside from that, the figures in that link are just plain wrong. Eg, it gives F-119 frontal area as 6.136 cm^2 (author of that link got his units wrong, should be 6136 cm^2 or 0.6136 m^2), which means an inlet diameter of just 34.75 inches; that's similar to the 34.8" diameter inlet for the F-100:

https://www.pw.utc.com/products-and-ser ... 00-Engine/The F-119 would be similar to the F-135 (as the F-135 was developed from the F-119), which according to Pratt and Whitney, has an inlet diameter of 43 inches and maximum diameter of 46 inches:

http://newsroom.pw.utc.com/download/me_ ... _pcard.pdfPratt doesn't give inlet or maximum diameter dimensions for the F-119, but other sources indicate it is around the same as the F-135:

45" diameter;

https://www.forecastinternational.com/a ... _RECNO=901 46" diameter;

http://www.deagel.com/Propulsion-System ... 20001.aspx46" diameter;

http://all-aero.com/index.php/contactus ... itney-f119The link gives the EJ200 as having a a 3.848 cm^2 inlet area, which calculates to approximately 27.5" inlet diameter, yet MTU Aero Engines gives the fan diameter as 29" / 740mm

https://www.mtu.de/fileadmin/DE/7_News_ ... /EJ200.pdfTook a while to find the maximum diameter of the EJ200, but this article has it at 0.85 meters:

https://www.flugrevue.de/flugzeugbau/tr ... 200/470931 which gives a frontal area of 5674.5 cm^2

The F404 has a maximum diameter of 35":

https://www.geaviation.com/sites/defaul ... Family.pdfAs does the F414:

https://www.geaviation.com/sites/defaul ... Family.pdfResulting in those engines having a frontal area of 6207.2 cm^2

And lol, the author of that link gave the AL-41 175 kN... which is the power rating of the izdeliye 30, not the 142 kN of the AL-41F-1S or 147 kN for the AL-41F1.

Here's better figures for maximum thrust / frontal area:

EJ200; 0.5674 m^2, 90 kN = 158.60 kN/m^2

F404; 0.6207 m^2, 78.7 kN = 126.79 kN/m^2

F414; 0.6207 m^2, 97.9 kN = 157.72 kN/m^2

F119; 1.0722 m^2, 156 kN = 145.50 kN/m^2

F135; 1.0722 m^2, 190 kN = 177.21 kN/m^2

AL-31F; 1.2868 m^2, 123 kN = 95.59 kN/m^2

AL-41F-1S; 1.2868 m^2, 142 kN = 110.35 kN/m^2

So the F414 is actually comparable in thrust/frontal area to the EJ200, while the F135 is clearly far better. And the Russian AL-41 is outclassed by the decades older F404.