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Description
Original F-16 , courtesy of darthpanda, and also a re-upload and a remaster from Photobucket.
It took me a while to graft the DSI into the F-16, which took some careful scaling.

Initial research into the DSI was done by Lockheed Martin in the early 1990s. The first Lockheed DSI was flown on December 11, 1996 as part of a Technology Demonstration project. It was installed on a F-16 Block 30 fighter, replacing aircraft's original intake diverter. The modified F-16 demonstrated a maximum speed of Mach 2.0 (Mach 2.0 is the F-16's clean certified maximum speed) and handling characteristics similar to a normal F-16. It was also shown that subsonic specific excess power was slightly improved.

GENERAL CHARACTERISTICS

    Crew: 1
    Length: 49 ft 5 in (15.06 m)
    Wingspan: 32 ft 8 in (9.96 m)
    Height: 16 ft (4.88 m)
    Wing area: 300 ft² (27.87 m²)
    Airfoil: NACA 64A204 root and tip
    Empty weight: 18,900 lb (8,570 kg)
    Loaded weight: 26,500 lb (12,000 kg)
    Max. takeoff weight: 42,300 lb (19,200 kg)
    Internal fuel: 7,000 pounds (3,200 kg)
    Powerplant: 1 × Pratt & Whitney F100-PW-220/220E afterburning turbofan
        Dry thrust: 17,155 lbf (76.3 kN)
        Thrust with afterburner: 28,600 lbf (127 kN)

PERFORMANCE

    Maximum speed:
        At sea level: Mach 1.2 (915 mph, 1,470 km/h)
        At altitude: Mach 2 (1,320 mph; 2,120 km/h) clean configuration
    Ferry range: 2,280 nmi (2,620 mi; 4,220 km) with drop tanks
    Service ceiling: 50,000+ ft[3] (15,240+ m)
    Rate of climb: 50,000 ft/min (254 m/s)
    Wing loading: 88.3 lb/ft² (431 kg/m²)
    Thrust/weight: 1.095 (1.24 with loaded weight & 50% internal fuel)
    Maximum g-load: +9.0 g

Description
Original F-16 , courtesy of darthpanda, and also a re-upload and a remaster from Photobucket.
It took me a while to graft the DSI into the F-16, which took some careful scaling.

Initial research into the DSI was done by Lockheed Martin in the early 1990s. The first Lockheed DSI was flown on December 11, 1996 as part of a Technology Demonstration project. It was installed on a F-16 Block 30 fighter, replacing aircraft's original intake diverter. The modified F-16 demonstrated a maximum speed of Mach 2.0 (Mach 2.0 is the F-16's clean certified maximum speed) and handling characteristics similar to a normal F-16. It was also shown that subsonic specific excess power was slightly improved.

GENERAL CHARACTERISTICS

    Crew: 1
    Length: 49 ft 5 in (15.06 m)
    Wingspan: 32 ft 8 in (9.96 m)
    Height: 16 ft (4.88 m)
    Wing area: 300 ft² (27.87 m²)
    Airfoil: NACA 64A204 root and tip
    Empty weight: 18,900 lb (8,570 kg)
    Loaded weight: 26,500 lb (12,000 kg)
    Max. takeoff weight: 42,300 lb (19,200 kg)
    Internal fuel: 7,000 pounds (3,200 kg)
    Powerplant: 1 × Pratt & Whitney F100-PW-220/220E afterburning turbofan
        Dry thrust: 17,155 lbf (76.3 kN)
        Thrust with afterburner: 28,600 lbf (127 kN)

PERFORMANCE

    Maximum speed:
        At sea level: Mach 1.2 (915 mph, 1,470 km/h)
        At altitude: Mach 2 (1,320 mph; 2,120 km/h) clean configuration
    Ferry range: 2,280 nmi (2,620 mi; 4,220 km) with drop tanks
    Service ceiling: 50,000+ ft[3] (15,240+ m)
    Rate of climb: 50,000 ft/min (254 m/s)
    Wing loading: 88.3 lb/ft² (431 kg/m²)
    Thrust/weight: 1.095 (1.24 with loaded weight & 50% internal fuel)
    Maximum g-load: +9.0 g