General Dynamics F-16 Fighting Falcon
Type: F-16A
Function: fighter
Year: 1976
Crew: 1
Engines: 1 * 105.7kN P&W F100-PW-220
Wing Span: 10.00 m
Length: 15.03 m
Height: 5.09 m
Wing Area: 27.90 m2
Empty Weight: 7387 kg
Max.Weight: 17010 kg
Max. Speed: Mach 2.05
Ceiling: 16750 m
Max. Range: 3900 km
Armament: 1*g 20 mm 9276 kg payload
Unit cost: 20 million USD
Type: F-16C/D Fighting Falcon
Country: USA
Export: Bahrain/Greece/Israel/Egypt/NZ/UAE/Singapore/South Korea/Oman/Chile
Function: Multirole Fighter
In Service date: 1979
Crew: 1
Engines: 1 x 131,6 kN (29590 lbs) General Electric F110
Wing Span: 10.00 m
Wing area: 27.88 m2
Wing Aspect Ratio: 3.09
Length: 15.03 m
Height: 5.03 m
Empty Weight: 8581 kg
Internal Fuel Weight: 3105 kg
Max.Weight: 19187 kg
Maximum Speed: Mach 2.0
Ferry Range: 4215 km
Combat Radius: 900 km
Internal Armament: 1*g 20 mm
G-limits: 9/-3.5
Maximum instantenous turn rate: 26 degrees/second
Maximum sustained turn rate: 18 degrees/second
TWR(50% fuel, 2 EM A2A missile, 2 IR A2A missile): ~1.26:1
TWR(100% fuel, 2 EM A2A missile, 2 IR A2A missile): ~1.1:1
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17 deg sustained turn rate is the initial ASR set for LCA mk-1 just 1 degree less than F-16 block C/D.
1.Even with 6G and 20 deg AOA limitation the LCA has already completed a horizontal loop in Aeroindia demo within 23 seconds. That comes to a STR of close to 16 deg with the limitations of partially opened flight envelope.We don't know whether the plane was stretched even to this partial limit of 6Gs and 20 Deg AOA in that demo.
Also with the same 6G 20 deg AOA restriction it completed a vertical loop within 20 seconds in AeroIndia 2013 ,meaning it had a STR of close to 18 deg in vertical loop. In a recent fly past the Su-35 too completed the powered vertical loop within 18 seconds. Once again We don't know whether the plane was stretched even to this partial limit of 6Gs and 20 Deg AOA in that demo.
Recent reports in a blog indicate that LCA mk-1 has achieved a Sustained Turn Rate to the IAf's satisfaction even with 1 ton extra empty weight than the original target of 5470 kg. SO it must have improved over the aeroindia2013 demo in a substantial manner.
So in no way can the initial airframe design can be called draggy.
Also the TWR ratio of LCA with 50 percent fuel is 1.07. Same for F-16 is 1.25. So with even lower thrust to weight ratio than F-16 C/D , LCA has managed to pull closer to the F-16 C/D .
In mk-2 it will only further improve, with weight reduction due to more composite percentage and a 20 percent higher thrust engine in GE F414 IN S 6. Since the length of fuselage is going to be expanded by 0.5 meter only it won't add to much empty weight either.
Also with an empty weight of 8.5 ton F-16 C/D carries 3.1 ton fuel.
LCA mk-1 with it's empty weight of 6.4 tons carries 2.5 ton fuel.SO LCA mk-1 has a close to 10 percent better fuel fraction ratio than the F-16 C/ D. Indicating it won't suffer much in range in an air to air configuration of 2 ton air to air missile load which is it's primary role.
But by having a significantly lower wing loading than the F-16 C/D Tejas mk-1 will have a much better Instantaneous turn Rate than the 26 degree given for F-16 C/ D.
Even the initial ASR given for LCA by MSD Woollen indicates a requirement of 30 deg maximum attainable in the ADA website.
So in the all important high off bore sight WVR missile launching capacity based on Instantaneous Turn Rate , it will be better than the F-16 C/D, just going by the low wing loading factor alone.. But needs citation ofcourse