June 11, 2010 at 11:54 am
I’ve had a Viper pilot tell me the F-16 can supercruise no problem. The Hornet’s advertised max cruise speed at alt (non-afterburner) is 1.1M
I don’t know the conditions, probably for a clean aircraft maybe without even pylons, maybe this was determined in development testing or perhaps a routine service performance I’ve no idea.
When the Viper pilot mentioned this he was having a dig at the popular marketing of supercruise and how important it seems to have become among enthusiasts. He said, it’s a bit silly, lots of modern warplanes, pretty much anything with a very high dry thrust/weight can supercruise (I suppose I should stipulate the role of a clean supersonic airframe too).
Okay it’s a given the ca.1.5M supercruise of the F-22 is impressive and remarkable, presumably other aircraft capable of supercruise just manage supersonic. It’s about ~400km/h bonus without the burners.
Traditionally older aircraft like the Phantom need to be on the burner to get supersonic. Lots of larger modern aircraft like the Eagle will need it if they’ve got a big load. But lighter aircraft with good thrust/weight even dry, like the F-16, Hornet and MiG-29 or late version MiG-23 presumably don’t have much of a problem unless carrying bombs.
So my question is naturally, the F-35 with such a good power/weight and a fairly clean airframe, why wouldn’t this aircraft supercruise? If a Viper can do it, surely it will. I mean maybe not ca.1.5M but certainly the 1.1M capability of the Hornet.
Is there some reason I’m not seeing as to why the F-35 might not supercruise?
By: FBW - 2nd December 2016 at 19:09
Transonic region- Straight wing
[ATTACH=CONFIG]250029[/ATTACH]
Swept wing will have lower overall wing wave drag- delay of drag rise:
[ATTACH=CONFIG]250030[/ATTACH]
Supersonic Vs Subsonic drag:
[ATTACH=CONFIG]250031[/ATTACH]
Note- While wing wave drag will be delayed and lower with a swept wing (and that is the largest contributor to wave drag), drag coefficient will still be much higher in the transonic. Beyond mach 1.2 Cd is relatively constant for most aircraft ( though drag will increase with speed)