Performance
Performance figures below are Van’s published numbers for the RV-10 with a 260 HP engine, augmented with N720AK-specific test data where available. Treat the published figures as a planning reference; verify against actual aircraft performance over the course of Phase I and ongoing operation.
V-Speeds (Reference)
See Section 2 for authoritative values. Quick reference:
| Speed | Value |
|---|---|
| V~S0~ (flaps 33°, ~2,190 lb test) | 48 KIAS |
| V~S~ (flaps 16°, ~2,190 lb test) | 56 KIAS |
| V~S1~ (flaps up, ~2,190 lb test) | 61 KIAS |
| V~G~ (best glide, prop full coarse) | 95 KIAS |
| V~X~ (best angle of climb) | 80 KIAS |
| V~Y~ (best rate of climb) | 95 KIAS |
| V~FE~ (max flap extended) | 90 KIAS |
| V~A~ (maneuvering, max gross) | 125 KIAS |
| V~NO~ (max structural cruise) | 158 KIAS |
| V~NE~ (never exceed) | 200 KTAS |
Stall and Approach Speeds
Stall speeds at ~2,190 lb test weight, level flight, idle power. At max gross (2,700 lb), add approximately 10%.
| Configuration | V~S~ | 1.3 × V~S~ (Approach) |
|---|---|---|
| Flaps Up | 61 KIAS | 79 KIAS |
| Flaps 16° | 56 KIAS | 73 KIAS |
| Flaps 33° (full) | 48 KIAS | 62 KIAS |
Operationally we fly OnSpeed AOA (solid tone) for normal approach and slow tone (drag-it-in) for short field; see OnSpeed.
Takeoff Performance
Van’s published ground-roll figures, sea level, ISA, no wind, paved runway. Van’s does not publish a 50 ft obstacle distance for the RV-10.
| Weight | Ground Roll |
|---|---|
| 2,200 lb | 360 ft |
| 2,700 lb (gross) | 500 ft |
Apply standard corrections for density altitude, wind, runway slope, and surface (grass adds ~15%). For obstacle clearance, plan generously — the 50 ft figure is generally 1.5–2× ground roll for piston singles.
Climb Performance
Van’s published rate of climb at sea level, ISA, full power:
| Weight | Rate of Climb | Service Ceiling |
|---|---|---|
| 2,200 lb | 1,950 fpm | 24,000 ft |
| 2,700 lb (gross) | 1,450 fpm | 20,000 ft |
In practice, climb at V~Y~ (95 KIAS) until 1,000 AGL, then transition to cruise climb at 120 KIAS, full throttle, 2,500 RPM. Reduce climb angle or richen Fuel Trim if CHT approaches 400 °F.
Cruise Performance
Van’s published cruise (260 HP, 8,000 ft, ISA):
| Power Setting | Light (2,200 lb) | Gross (2,700 lb) |
|---|---|---|
| 75% | 175 KTAS | 171 KTAS |
| 55% | 156 KTAS | 153 KTAS |
Operationally we cruise at full throttle / 2,400 RPM with Fuel Trim 0% at altitudes from 6,000 to 12,000 ft. Verify actual TAS, fuel flow, and CHT against the EFIS as the airframe accumulates hours.
Landing Performance
Van’s published ground-roll figures, sea level, ISA, no wind, paved runway, max braking. Van’s does not publish a 50 ft obstacle distance for the RV-10.
| Weight | Ground Roll |
|---|---|
| 2,200 lb | 525 ft |
| 2,700 lb (gross) | 650 ft |
For short-field landing, fly the slow tone with power for descent control (drag-it-in technique); see Section 5 → Short Field Landing.
Range and Endurance
Van’s published range at 8,000 ft, no reserves, full 60 gal fuel, gross weight:
| Power | Range | Time |
|---|---|---|
| 75% | 717 NM | ~4.2 hr |
| 55% | 869 NM | ~5.7 hr |
Plan a 45-minute reserve at cruise burn for night/IFR (FAR 91.167), 30-minute reserve for day VFR (FAR 91.151), or longer per personal minimums.
Glide Performance
Best glide is 95 KIAS with the propeller pulled to full coarse (low RPM). Pulling the prop coarse reduces drag substantially compared to leaving it at high RPM — this is the difference between a usable glide and falling out of the sky.
Confirm actual glide ratio and altitude loss with at-altitude glide tests during Phase I and ongoing operation. Record altitude lost per 360° turn at 20°, 30°, 45° bank for use in pre-takeoff turnback briefing planning per the EAA Power-Loss-on-Takeoff Working Group methodology.
Add 250–500 ft pad to measured 360° altitude loss to define “high key” altitude for turnback feasibility — see Vac’s working-group writeup.