well its hard to discuss LCA and JF17, one is in production and other one in development stages. India first need toresolve the weight and engine thrust ratio, because engine does not have enough thrust for LCA over all weight.
Again little facts, more imagination(Srce: Wikipedia):
PLEASE BE FACTUAL FOR GODS SAKE!
JF-17
Powerplant: 1× Klimov RD-93 turbofan [37]
Dry thrust: 49.4 kN [38] (11,106 lbf)
Thrust with afterburner: 81.4 kN [39] (18,299 lbf)
G-limit: +8.5 g [13]
Fuel Capacity: 2300kg (5,130 lb) [40]
Performance
Maximum speed: Mach 1.8 [41] [42]
Combat radius: 1,352 km [43] (840 mi)
Ferry range: 3,000km [44] [45] (1,864 mi)
Service ceiling 16,700 m [46] (54,790 ft)
Thrust/weight: 0.95 [47] [48]
Hal Tejas
Loaded weight: 8,500 kg (18,700 lb (in fighter configuration))
Max takeoff weight: 14,500 kg (32,000 lb)
Powerplant: 1× General Electric F404-GE-IN20 turbofan
Dry thrust: 54.9 kN (12,250 lbf)
Thrust with afterburner: 85 kN (19,000 lbf)
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: 3000 km (1,840 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