Bring_it_on.
I believe Over G is referring to the fact no aircraft can hide against a radar with a wavelength of the order of the aircraft itself. However, the resolution provided by said radar return will be poor.
However, if multiple emitters/recievers at multiple locations are used, it may [emphasis on may] be possible to combine the information to provide further localisation.
Oh and Over G has made a good point [well kinda].
How much range does your typical missile IR sensor have?
I’m thinking along the lines of using low freq radar to get the approximate position of a stealthy aircraft – you then hoist a IR SAM in the direction, giving it guidance from your radar. Would the IR sensors have sufficient range to cover the ground that the radar cannot resolve down to?
Another benefit would be that the intruding aircraft would not know it has been fired upon.
Flawed for a couple reasons. 1. They’d be using something like JASSM or JASSM-EX not an F-22 with bombs. and 2. instead of being able to defend a target with one battery now you’re going to need 5 or 6 because you need the one in the middle and rest to surround it. And their bubbles will be relatively small which will compound the problem. So in essence you’ve squandered your SAM batteries to defend against a target that is elsewhere. How is that a good idea?
1. Whatever, its still gonna be detected before it gets to the SAM radar position – and it can be taken out by Tors etc.
2. So what. How much does 7 SAM systems cost in comparison to an F-22 (or whatever) and the logistical train?
3. Their bubbles will be relatively small compared to the bubble for a non-VLO aircraft. However, since the range for S-300/S-400 is measured in hundreds of miles, I’ll happily assume a detection distance of 40.
I’ve “squandered” my SAM batteries defending a target… thats something the other guy wants to hit… and hit it for a reason. Be it a bridge, a power station, a communications centre, whatever – he can’t hit it, and that’ll **** him off.
The best way to get over a hangover is to never get to a point where you can get a hangover –
In other words , keep drinking!!!
As much as i would enjoy that, I think my wallet might protest (again) :diablo:
Exactly.
All just reinforces the fact we are all talking sh*te 😀
Just to answer a few comments in the thread [but I’m well hungover, so could get things a little muddled :D]
– Normally every aircraft has a flight envelope and a departure from controlled flight. However, new aircraft [such as the F-22 and OVT] have carefree handling as a design objective. Basically, this means the pilot can do what he wants in terms of flying the aircraft, and he will always retain a good measure of control authority over the aircraft. Therefore departure from controlled flight is impossible in an F-22 or OVT [or similar such aircraft].
– As far as I knew, the F-16 was AoA limited by lateral stability, its vertical fin induces problems in manouvering. A quick google found this: here. Its well worth a read.
– Also, fluidic TVC… From what I’ve read its still some way short of the efficiency of mechanical systems, and there are doubts as to whether the deficiencies can be overcome.
– Firebar is right in saying that manouverability is affected more by an aircraft’s aerodynamics than its fly-by-wire capabilities. However, he is wrong in saying the F-22 has to have a limit to its AoA. There is no reason why it should.
I was gonna say more, but my head is killing me 😮
Errr…. isn’t the solution kinda obvious?
You are all assuming a solitary SAM radar/launcher. What if its a web of radars and launchers.
You have one SAM radar up and emitting, with several [emitters and launchers] surrounding it at a good distance [say 50 miles], these radars are shut down.
The F-22 may be undetectable to the emitting radar, but as soon as the JDAM/SDB etc is launched, it will detect both aircraft and bomb [and thereafter just the bomb once the doors are closed again]. The position is relayed to the appropriate outlying emitters/launchers, which then light up their radars, get the F-22 5 miles away and fire…
Scratch one [or more in the flight] F-22s.
A little imagination goes a long way. 🙂
Can I just make a point on the stupidity of saying something is “limited” in service.
Do you really think a pilot is going to give 2 ****s about the manual when they has an R-77 or similar boring in? Get real!!!
Since its carefree handling they’ll do any and every manouvre they can think of to evade!
In war, peacetime limits go out the window.
I think if fought today, on the airwar side you could reasonably expect more casualties on the side of the USAF. After all, SAMs have moved on, while the means of “targetting” a hidden enemy inside a dense jungle is still the same [napalm drops yes?]. While the airpower of the North Vietnamese would would have quickly been destroyed, the ground based defenses would be much more enduring IMO.
As far as the ground war goes, the events in Lebanon recently with regards the proliferation of effective anti-tank weapons should be more than enough proof.
Bottom line, In my opinion, the US would have sustained much heavier casualities.
What use is stealth and supercruise against guys hidden in a dense jungle?
Originally Posted by sferrin
So no matter how much power you have dry thrust will get you to Mach 1.72 but not Mach 2 huh? Is that like the lightspeed barrier or something? :rolleyes:((2.0 * 300m/s)² – (1.72 * 300m/s)² )/(1.72 * 300m/s)² * 100
= 35% more drag. That is something, ain’t it?
Don’t argue with the air density, with every feet you climb your losing power exactly as fast as you lose drag.
Schorsch, your right in your post [if 300 m/s is well below M=1.0], but supersonic drag is proportional to a helluva lot more than V^2. [according to linearised theory the drag coefficient of the aerofoil section is proportional to the AoA^2, whereas in subsonic flow drag is proportional to the AoA].
So if you’d a wing setting angle of 2 degrees, you can double your Cd number before going to D = Cd*(0.5*rho*V^2*S), that would mean drag is proportional to 2*V^2.
While use of the area rule reduces transonic drag rise by around a factor of 2, its still a 2-3 times increase on the subsonic drag values.
No idea whether the F-22 has the thrust to overcome the drag rise or not, but I’d reckon we’d have heard about it before now.
I suppose there is another possibility I didn’t put down.
War itself is obsolete [well, at least as far as war between technologically developed sovereign nations on this planet go].
Lets face it, if two countries advanced enough to do the above do have a square go at each other, it’ll get real ugly, real quickly, and the next war after that will more than likely be fought with sticks and stones.
Perhaps the wrong thread to ask in, but does anyone know the static margin of the F-16? Is the figure of -5 % correct?
As far as I was aware, different F-16s had different static margins.
I think the F-16A had a negative static margin, but all after had reduced static margins instead.
Can anyone confirm this either way?
^ in regards to the aerodynamics.. wouldn’t the canards create vortexes that’ll damage the canted vertical stabilizers? Where’s Vortex when ya need him :diablo:
No, I don’t think they would. The canard wingtips are quite far outside the stabiliser locations.
Awwww, not this again. I think there are around 50 pages devoted to this somewhere on the forum already!
Talking about inlet performance in the transonic/supersonic regime: You *need* a variable inlet, otherwise you will have a design optimized for *just one* flight regime. It’s an operational trade-off (weight/maintenance vs mach-related performance) and the USN decided higher mach performance is not important. Not entirely wrong given the way they operate these jets as bomb/PGM-trucks.
You can bleed off air within the inlet, downstream of the normal shock so you obtain your ideal mass flow rate. Thats what they do on the F-22. Key is making sure the flow is nice and neat avoid distortions on the fan face.
The F-22 has an oblique shock from the upper intake, the normal shock is controlled by the dump valve, and the duct is designed to keep the flow right to the fan face.
Variable geometry designs are no longer a necessity.