Search results for query: afterburning J52

Thing is you DON'T need a afterburner for a J52 F-5. It's dry thrust depending on model goes from equal to the max thrust installed in the Canadian F-5As (8,500 to 8,600) to 20% more than F-5E (12,000 to 10,000). You just made F-5... supercruising.

Considering that an afterburning J52 was one of the engines considered for one of the FC-1s predecessor designs, I don't think it too outlandish, esp. since there was an afterburning version of its turbofan cousin. For a MiG-21 'clone', a J79 makes a lot of sense since it's much the same type...

I found these information about the non-afterburning derivatives of the General Electric F404 turbofans in Turbofan and Turbojet Engines: Database Handbook (2007) by Élodie Roux: SOURCE: Roux, Élodie. (2007). Turbofan and Turbojet Engines: Database Handbook (pp. 181, 183). Blagnac, France...

I remember something like that convo in regards a low end version of the super tiger for non nato nations and a single engine F-5 yeah it would have been a totally sweet little package given that the J-85 on AB was a thirsty little hippo EDIT: Another fun one, though utterly irresponsible and...

Well, bugger. Okay, afterburning J52 in the "single engine F-5E/F". If people buy lots of those, then you can look at swapping the J52 with the F404 for some F-5G/Hs among everyone who bought the F-5E/Fs in the mid 1980s.

In the short term, fitting the 11,200 lb.s.t. J52-408 with an afterburner (or using J79s) would have powered at least prototypes of most F-404-powered aircraft. It also depends on where you kill the engine... at the GE1 (initial concept prototype) stage? The YJ101 (engine that powered the...

Eh, I wouldn't take the RM8 as much of a basis for J52 development. The Swedes almost entirely redesigned the JT8D to make it suitable for supersonic flight - it got new fans, turbines, fuel control, and a new combustion chamber. However, there was one afterburning variant, designed by the...

http://www.flightglobal.com/pdfarchive/view/1987/1987%20-%201876.html

And a J52 with an afterburner almost made it as the PW1216 for the aborted "Super -7". I have seen Northrop's response to IAI on the Lavi, working from the original concept with the F404. Northrop proposed a couple different blendings of the Lavi with the F-5G/F-20 and taking advantage of the...

With the AB, the Atar 9 was about 6.2m vs the 8 at 3.9m or so. I may be wrong here, but weren't the ABs of the time for comparable turbojets all about 2m in length? Also, the IVB had an Avon and for the SuE, the J52 was seriously considered. But AFAIK, never an afterburning engine. My...

Hi guys ... I need some help regarding the engines under consideration for the very early "Sabre II" / "Super-7" because I found some very crude "babelfish" translations of early engine-"competition" when Western assistance was still under way ! All what I could extract is that there were the...

Would it still have been twin engined, or would it be able to achieve Mach 2 using a single higher thrust afterburning engine?

J52: -6A/B (early A-4E & A-6A/EA-6A): 2,056lb weight, 8,500 lb thrust. -8A/B (late A-4E/A-4F & A-6E/KA-6D): 2,118 lb weight, 9,300 lb thrust. -408 (A-4M & EA-6B): 2,318 b weight, 11,200 lb thrust. F404-100D (F-117 & A-4SU*): 1,830 lb weight, 11,000 lb thrust. F412 (A-12): 13,000 lb thrust -...

The high bypass engine pictured has a center tailcone, but I think this is more of a flow director as part of the core flow / fan flow integration, since the exhaust flow is unlikely to be supersonic. The Hound Dog missile with the J52 turbojet definitely had a plug nozzle since the nozzle...

It seems several efforts were made to exploit Mach 2 performance in the Marut. William Green in his 1964 edition of 'The World's Fighting Planes' mentions the Mk2. The USSR had offered the RD-9F but apparantly becuase the Soviets were unwilling to develop the type further beyond its M1.4...

Specs for the J52-P-408A, the immediate predecessor of PW1212: Dry Thrust: 11,200lb st (49.8kN) Mass flow: 65kg/sec Length: 3.02m Diameter: 0.81 Dry mass: 1053kg Pressure ratio: 14.6:1 Config: 5/7/1/2 Combustor: cannular SFC: approx 0.9 T/W ratio: 4.83 Pressure rise per stage: 1.25:1 For...

That’s a good thought! You could also skip the development costs of a J52 afterburner and engine fitment with a higher thrust J65/Sidney Sapphire found in the Gloster Javelin: 11,000 dry and 12,300 wet. A big jump in thrust from 7,500 dry and 10,500 wet while using older tech.

Singaporean A-4SU. The base -S model adds two more wing hardpoints, cockpit armor, spoilers, Sidewinder capability, and DEFA cannons. The two-seater TA-4S got a 28" fuselage stretch with a stepped instructor's seat in back so they can see better. Interestingly, these kept the J65 of the...

or given the diameter an adapted version of the AB on the J-65.. either way it would be about the size of a J-65, except this one would not SUCK! Taking a look at it by dividing the wet thrust by the dry thrust to give an idea of how much the AB boosts things... using either of the options gets...

According to Brad Elwood in his Crowood volume on A-4 Skyhawk: