The primary advantage of the delta wing design is that the wing's leading edge remains behind the shock wave generated by the nose of the aircraft when flying at supersonic speeds, which is an improvement on traditional wing designs. While this is also true of highly swept wings, the delta's planform carries across the entire aircraft, allowing it to be built much more strongly than a swept wing, where the spar meets the fuselage far in front of the center of gravity. Generally a delta will be stronger than a similar swept wing, as well as having much more internal volume for fuel and other storage.
Another advantage is that as the angle of attack increases the leading edge of the wing generates a vortex which remains attached to the upper surface of the wing, giving the delta a very high stall angle. A normal wing built for high speed use is typically dangerous at low speeds, but in this regime the delta changes over to a mode of lift based on the vortex it generates. The disadvantages, especially marked in the older tailless delta designs, are a loss of total available lift caused by turning up the wing trailing edge or the control surfaces (as required to achieve a sufficient stability) and the high induced drag of this low-aspect ratio type of wing. This causes delta-winged aircraft to 'bleed off' energy very rapidly in turns, a disadvantage in aerial maneuver combat and dogfighting. This can solved with relaxed stability, strakes and canards.
Wings and Configurations for High-Speed Flight
Swept Wings The critical Mach number of a wing is the flight Mach number of the aircraft at which the local Mach number at some point of the wing becomes 1.0. At a Mach number slightly in excess of this critical value, shock waves form on the wing, and further increases in speed cause [249] large changes in the forces, moments, and pressures on the wing. The effects on the lift and drag characteristics of increasing the Mach number beyond the critical value are briefly discussed and illustrated in chapter 5. Subsonic aircraft usually do not cruise at Mach numbers much beyond the critical value. For supersonic flight, however, the aircraft must have sufficient power to overcome the high drag in the transonic speed range and be capable of controlled flight through this capricious Mach number range. link
Mach angle (NASA SP-7, 1965) The angle between a Mach line and the direction of movement of undisturbed flow. See Mach wave.
Mach wave (NASA SP-7, 1965) 1. A shock wave theoretically occurring along a common line of intersection of all the pressure disturbances emanating from an infinitesimally small particle moving at supersonic speed through a fluid medium, with such a wave considered to exert no changes in the condition of the fluid passing through it. The concept of the Mach wave is used in defining and studying the realm of certain disturbances in a supersonic field of flow. 2. A very weak shock wave appearing, e.g., at the nose of a very sharp body, where the fluid undergoes no substantial change in direction. link wave
Quote: in the mainly turn oriented energy regime, (underpowered engine you forgot to quote, H.)
Quote: Exactly what I said, poster, but without the uncited and unacknowledged fluff from ypir plagiarozed source . Who doesn't know aeronautics here?
NASA/DRYDEN defines the aerodynamics of F-22 and F-35, they WRITE the book in PLAIN American English but obviously your bunch is NOT interested the slightest...
Time to go to your nearest flying school and borrow the books, in aeronautic language this phrases means nothing else than "i dont know what i am writing" but i SURE can flame...
Quote: Since I don't have to hunt for this stuff...
You should LEARN because you cant even comprehend what you copy/paste...
Quote: And for a novice like you: wiki is good enough.
AGAIN you are the novices here...
The sources i am using are the only authorities on the subject, meaning before puting even a begginer on an aircraft youy have to learn your theoprical basics, it helps understanding the complex stuff which is way above your newbbies heads.
And BTW the best example of it is your quest for the Delta wing when the best sources available simply talk about wing sweep.
There is no need for a delta design to obtain a high Critical Mach.
Quote: By the wey, you are a liar.
As I plainly showed here.
Really? WHERE?
You keep taking your low standard for a granted worl'ds avereage, think again i posted the links to these articles on this very particular subject...
Dont mystake ME for one of yours, you're simply not up to it, your bunch have to ressort to spin ,twist and reverse psychology, calling people names which in reality applies best to yourself....
The critical Mach number of a wing is the flight Mach number of the aircraft at which the local Mach number at some point of the wing becomes 1.0. At a Mach number slightly in excess of this critical value, shock waves form on the wing, and further increases in speed cause [249] large changes in the forces, moments, and pressures on the wing. The effects on the lift and drag characteristics of increasing the Mach number beyond the critical value are briefly discussed and illustrated in chapter 5. Subsonic aircraft usually do not cruise at Mach numbers much beyond the critical value. For supersonic flight, however, the aircraft must have sufficient power to overcome the high drag in the transonic speed range and be capable of controlled flight through this capricious Mach number range.
The angle between a Mach line and the direction of movement of undisturbed flow. See Mach wave.
Mach wave (NASA SP-7, 1965) 1. A shock wave theoretically occurring along a common line of intersection of all the pressure disturbances emanating from an infinitesimally small particle moving at supersonic speed through a fluid medium, with such a wave considered to exert no changes in the condition of the fluid passing through it. The concept of the Mach wave is used in defining and studying the realm of certain disturbances in a supersonic field of flow. 2. A very weak shock wave appearing, e.g., at the nose of a very sharp body, where the fluid undergoes no substantial change in direction. link target="_blank">link wave
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