The Van's RV-7 and RV-7A are two-seat, single-engine, low-wing homebuilt airplanes sold in kit form by Van's Aircraft. The RV-7 is the tail-wheel equipped version, while the RV-7A features a nose-wheel.[4]
| RV-7 | |
|---|---|
 | |
| Role | RV-7 |
| Manufacturer | Van's Aircraft |
| Designer | Richard VanGrunsven |
| First flight | 2001[1] |
| Introduction | Early 2001[2] |
| Number built | 1910 (December 2022)[3] |
| Developed from | Van's Aircraft RV-6 |
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The RV-7 was the replacement of the RV-6, replacing the RV-6 in 2001.[5] It is externally similar to the earlier model, with longer wings, larger fuel tanks and a larger rudder to improve spin recovery characteristics.[6]
Development
Van's aircraft designer Richard VanGrunsven designed the RV-7 to replace the RV-6, which was a two-seat side-by-side development of the RV-4. In turn, this was a two-seat tandem version of the single seat RV-3.[7]
The RV-7 incorporated many changes resulting from the lessons learned in producing over 2,000 RV-6 kits. The RV-7 airframe will accept larger engines, including the Lycoming IO-390, up to 215 hp (160 kW).[8] The RV-7 also has increased wingspan and wing area over the RV-6, as well as more headroom, legroom and an increased useful load. The RV-7 carries a total of 42 US gallons (159 litres) of fuel, up from 38 US gallons (144 litres) on the RV-6.[7]
The RV-7 shares many common parts with the RV-8 and RV-9, which reduces production costs. The RV-7 has a computer-assisted design with pre-punched rivet holes, helping to keep assembly time to about 1500 hours for the average builder.[9]
The RV-7A version features a hardened, solid steel nose-wheel strut that fits into a tube welded to the engine mount. As in all nose-wheel equipped RV aircraft, the nose-wheel is free castering and the aircraft is steered with differential braking, or rudder at higher taxi speeds. The brakes are conventional toe brakes.
As of November 2022, 1,909 RV-7s and RV-7As had been flown.[3]
Specifications (RV-7)
Specifications are given for 200 hp, IO-360 configuration with a Hartzell constant speed propeller
General characteristics
- Crew: one pilot
- Capacity: one passenger
- Length: 20 ft 4 in (6.20 m)
- Wingspan: 25 ft (7.6 m)
- Height: 5 ft 10 in (1.79 m)
- Wing area: 121 sq ft (11.2 m2)
- Empty weight: 1,114 lb (505 kg)
- Gross weight: 1,800 lb (816 kg)
- Max takeoff weight: 1,800 lb (816 kg)
- Powerplant: 1 × Lycoming O-320, Lycoming O-360 or Lycoming IO-390 constant speed or fixed pitch, 160 to 215 hp (119 to 160 kW)
Performance
- Maximum speed: 217 mph (349 km/h, 189 kn) at sea level
- Cruise speed: 207 mph (333 km/h, 180 kn)
- Stall speed: 51 mph (82 km/h, 44 kn)
- Never exceed speed: 230 mph (370 km/h, 200 kn)
- Range: 765 mi (1,231 km, 665 nmi) at cruise 75% power at 8,000 ft (2,500 m)
- Service ceiling: 22,500 ft (6,900 m)
- Rate of climb: 1,900 ft/min (9.7 m/s)
- Wing loading: 14.8 lb/sq ft (72 kg/m2)
See also
Related development
Aircraft of comparable role, configuration, and era
References
External links
