Regret the late response, too tied up on work & family matters. Raman, you're absolutely right on there being no anhedral, and its clear in the following photos -Raman wrote:tsarkar,tsarkar wrote:
JE Menon...wings bent almost flexibly like a bird...
That is a deliberate design feature. Its a cranked anhedral and the only plane in the world to have it. Supposed to help with High AoA.
http://cdn-www.airliners.net/aviation-p ... 867325.jpg
http://newsonair.com/feature-image/LCA-tejas-header.jpg
In plain visual terms, when seen from the side, the inner wing is at an angle to the longitudinal axis of the aircraft. However, this wing angle or anhedral gradually reduces as we move spanwise along the wing. As we reach towards the outer span of the wing, angle becomes zero. The outer wing is actually parallel or in-line with the longitudinal axis of the aircraft. In theory, when the inner wing starts to stall at progressively higher AoA, the outer wing will still be at a slightly lesser AoA and provide sufficient lift. I'm not sure whether flight test results on the actual performance of this wingform have been published, but it'll be interesting reading.
I'm afraid that's not what anhedral is. Anhedral is the opposite of dihedral - it is, informally speaking, when the wing tips are lower than the wing roots when viewed head on. E.g., C-17 and IL-76 show pronounced anhedral. The primary reason for providing anhedral is lateral stability. Some high-wing swept-wing airplanes can be "too stable" and therefore difficult to maneuver because high wings and wing sweep both contribute to lateral stability. Anhedral decreases lateral stability. (In comparison, dihedral increases lateral stability.)
The phenomenon you are describing is called washout, when the sectional coefficient of lift is gradually reduced spanwise from root to tip. Washout can be geometric (where, the wing is actually "twisted" so the roots have higher angle of attack than the tips), or aerodynamic (where different airfoil sections are used along the span for the same effect), or (most often in today's airplanes) a combination of both.
Designers include washout for two reasons:
- As you correctly point out, it prevents the whole wing from stalling all at once.
- By having higher lift at the roots and lower lift at the tips, they are approximating an elliptical lift distribution along the span of the wing. The closer you can get the lift profile to match this elliptic lift distribution, the less your induced drag.
http://3.bp.blogspot.com/-YUs4s-3sfGs/U ... 747029.JPG The trailing edge makes it clear there is no anhedral. Infact, when it comes to the tips, I notice a slight negative incidence. More clear here http://www.bharat-rakshak.com/IAF/Image ... PV5-01.jpg & here http://www.bharat-rakshak.com/IAF/Image ... PV5-03.jpg
My description of the anhedral came from a conversation I had in late 80's / early 90's with someone associated with the program (Yes, I've been following the program keenly since the early 80's). He is well respected & knowledgeable in aeronautical engineering, and he did describe the anhedral wing as giving better maneuverability. It might be possible that during a later design iteration, the anhedral was dropped.
The LCA as a planform was designed for maneuverability. Those days, the US was gifting F-16s to Pakistan with an initial tranche of 32, followed by a second tranche of 28 (later blocked because of Pressler Amendment) followed by third & fourth tranches that would have taken numbers beyond 100. We made some panic purchase of MiG-23.
So when I hear/read about LCA not meeting design specifications, I try to understand what caused the gap between design specifications & actually achieved performance specifications.
One interesting piece of information I read was here http://en.wikipedia.org/wiki/Grumman_X- ... nstability
In this case, the flight control system moderated the instability to keep the aircraft stable, and consequently made it less maneuverable.The high pitch instability of the airframe led to wide predictions of extreme maneuverability. This perception has held up in the years following the end of flight tests. Air Force tests did not support this expectation.[5] For the flight control system to keep the whole system stable, the ability to initiate a maneuver easily needed to be moderated. This was programmed into the flight control system to preserve the ability to stop the pitching rotation and keep the aircraft from departing out of control. As a result, the whole system as flown (with the flight control system in the loop as well) could not be characterized as having any special increased agility.