Thread: A Few Quick Questions Regarding TWR and Engines...

Originally Posted by gabriel

the answer is no.

From Wikipedia,

JAS 39 - Gripen (Not Gripen-NG)
General characteristics
• Crew: 1 (2 for JAS 39B/D)
• Length: 14.1 m (46 ft 3 in)
• Wingspan: 8.4 m (27 ft 7 in)
• Height: 4.5 m (14 ft 9 in)
• Wing area: 30.0 m² (323 ft²)
• Empty weight: 5,700 kg (14,600 lb)
• Loaded weight: 8,500 kg (18,700 lb)
• Max takeoff weight: 14,000 kg (31,000 lb)
• Powerplant: 1× Volvo Aero RM12 afterburning turbofan
o Dry thrust: 54 kN (12,100 lbf)
o Thrust with afterburner: 80.5 kN (18,100 lbf)
• Wheel track: 2.4 m (7 ft 10 in)
• Length (two-seater): 14.8 m (48 ft 5 in)
Performance
• Maximum speed: Mach 2 (2,130 km/h, 1,320 mph)
• Combat radius: 800 km (500 mi, 432 nmi)
• Ferry range: 3,200 km (2,000 mi) with drop tanks
• Service ceiling 15,240 m (50,000 ft)
• Wing loading: 336 kg/m² (68.8 lb/ft²)
• Thrust/weight: 0.97


JF-17 Thunder/FC-1 Fierce Dragon
General characteristics
• Crew: 1 (2 for proposed twin-seater)
• Length: 14.0 m (49 ft)
• Wingspan: 9.45 m (31 ft)
• Height: 4.77 m (15 ft 8 in)
• Wing area: 24.4 m² (263 ft²)
• Empty weight: 6,450 kg (14,200 lb)
• Loaded weight: 9,100 kg including 2× wing-tip mounted air-to-air missiles (20,062 lb)
• Max takeoff weight: 12,700 kg (28,000 lb)
• Powerplant: 1× Klimov RD-93 turbofan
o Dry thrust: 49.4 kN (11,106 lbf)
o Thrust with afterburner: 81.4 kN (18,299 lbf)
• G-limit: +8.5 g
• Fuel Capacity: 2300kg (5,130 lb)
Performance
• Maximum speed: Mach 1.8
• Combat radius: 1,352 km (840 mi)
• Ferry range: 3,000km (1,864 mi)
• Service ceiling 16,700 m (54,790 ft)
• Thrust/weight: 0.95


HAL Tejas/LCA
General characteristics
• Crew: 1
• Length: 13.20 m (43 ft 4 in)
• Wingspan: 8.20 m (26 ft 11 in)
• Height: 4.40 m (14 ft 9 in)
• Wing area: 38.4 m² (413 ft²)
• Empty weight: 5,500 kg (12,100 lb)
• Loaded weight: 8,500 kg (18,700 lb (in fighter configuration))
• Max takeoff weight: 14,500 kg (31,967lb)
• Powerplant: 1× General Electric F404-GE-IN20 turbofan
o Dry thrust: 54.9 kN (12,250 lbs)
o Thrust with afterburner: 85 kN (19,000 lbs)
• Internal fuel capacity: 3000 liters
• External fuel capacity: 5×800 liter tanks or 3×1,200 liter tanks, totaling 4,000/3,600 liters
Performance
• Maximum speed: Mach 1.8+ (1,920+ km/h at high altitude) at 15,000 m
• Range: 2000 km (1,242 mi(without refueling))
• Service ceiling 15,950+ m (50,000 ft(Engine re-igniter safely capable))
• Wing loading: 221.4 kg/m² (45.35 lb/ft²)
• Thrust/weight: 1.02
• g limits : +9 g / -3.5 g

To which question are you responsing with this "no"?
If not, which part of the question is not clear to you? He was talking about the thrust/weight ratios of the three aircraft in question and why the thrust on the LCA is deemed insufficient.

PS - I would have answered the question myself if I had known the answer. From what I see, it puzzles me too.