SkyRunner eVTOL Flight Test 2022

SkyRunner eVTOL Flight Testing

124 flights (Logged below)

GENERAL PERFORMANCE

 

 

 

1. STALL (4.1.2.4):

V(s1) Stall Speed: MPH CAS

 Payload: UAV 0 lbs to 800 lbs useful 

*NOTE: Vso = Vs1

 

N/A

Initial: CSH

Reference Parameters: 

 

Compliance with 4.1.2.1

ALLPASS

Date: LOGGED

Initial: CSH

Straight and Level Stall Test – Pass 10/1/15 CSH lowest speed reach is = MPH CAS

Climb (full flare) – PASS

Climb (turn right) – PASS

Climb (turn left) – PASS

10/01/15 CSH

Descend (full flare) – PASS

Descend (turn right) – PASS

Descend (turning left) – PASS

10/01/15 CSH

Straight & Level (full flare) – PASS

Straight & Level (turn right) – PASS

Straight & Level (turn right) – PASS

10/01/15 CSH

 

 

 

 

      

 

Comments: The lower rigging cables were changed to geometrically move the control bar back 3 in. This was enough to get the wing to stall before the control bar touched the compression strut. The stall could be felt by a trembling in the control bar and the nose pitching down approximately 10°. The wing was held level within 5° during the stall. This yielded approximately 900 f/m sink rate during the stall.

 

 

CLIMB & GLIDE compliance with 4.1.2.2

PASS

Date: LOGGED

Initial: CSH

Vx Gradient of Climb

1:1.5 

Vy Rate of Climb 

840 FT/MIN  

The glide ratio is measured to be 3:1. Hence to descend 50’ would take 150’ horizontal distance and to flare and stop would take another 200’ (or less). Therefore, 50’ is needed to land from a 50’ height. 4.1.2.2 (2)

Comments:

Vx –The aircraft took off from runway 36 and a stabilized climb was 15 ft feet per second while moving from take off speed of 5 MPH CAS. 

VY – The aircraft took off from runway 18 and climb was established at the altitude 150 ft AGL. 

     

 

 

 

CONTROLLABILITY AND MANEUVERABILITY 4.1.2.3

DATE: LOGGED

INITIAL: CSH

GENERAL: When operating in accordance with the recommendations in the Aircraft Operating Instructions, the aircraft shall be safely controllable and maneuverable during the following scenarios without excessive pilot skills nor exceeding pilot forces of 20 lbs for prolonged application. 4.1.2.3 (1)

Conditions:

 

A. Takeoff at Maximum Takeoff Power

PASS

DATE: 

LOGGED

INITIAL: CSH

Comments: Throttle was advanced to full. At 4300 RPM the carriage lifted off smoothly and controllably. 
Pitch was controlled only by the RPM and the nose angles up approximately 10 for best climb.  

B. Climb

PASS

DATE: LOGGED

INITIAL: CSH

Comments: the aircraft was completely hands-off stabilized climb at full throttle. 

C. Level Flight

PASS

DATE: LOGGED

INITIAL: CSH

Comments: Power was reduced to 5600 rpm straight and level flight yielded 38 mph CAS (hands off for 22 sec, 42 seconds and 30 seconds)

D. Descent

PASS

DATELOGGED

INITIAL: CSH

Comments: Power was reduced to an idle and a stabilized descent was established. A stabilized hands-off descent at 38 mph CAS was established 

E. Landing, Power On And Off

PASS

DATE:  LOGGED

INITIAL: CSH

Comments:

Power On – On short final at 3 mph using 3000 rpm with a stabilized approach descending 550 f/m. The descent was slowed at 20’ feet above ground level until holding altitude 24 in off the ground. Throttle was then reduced to idle and the aircraft settled onto the ground approximately 6 sec later. VIDEO 

 

Power Off – On short final at idle sinking 500 f/m. 

 

 

 

ST

LONGITUDINAL STABILITY 4.1.3.1, 4.1.3.2

 

 

PASS

DATE:LOGGED

INITIAL: CSH

4.1.3.1 Longitudinal stability of the aircraft will be demonstrated by performing 120 seconds of flight without control input for three conditions. In each case, the aircraft must not enter into dangerous or unusual attitudes. Test must be conducted at maximum gross weight, with minimum of in-flight turbulence. 

4.1.3.2 The three conditions are:
(1) Maximum power setting climb, (2) Zero power descent, and
(3) Cruise setting power level flight. 

 Conditions:

Comments:

     

 

 

LATERAL & DIRECTIONAL STABILITY 4.1.3.3

 

 

PASS

DATE: LOGGED

INITIAL: CSH

4.1.3.3 Lateral and Directional Stability:

(1) 
Lateral stability will be demonstrated by maintaining the controls in a neutral position, which will initially give an unaccelerated level flight condition. The aircraft must not enter into a dangerous attitude during the 2 min that the flight controls are fixed. Test must be conducted at maximum takeoff weight, with minimum of in-flight turbulence. 

(2) Directional stability will be demonstrated by a separate and full deflection of each directional flight control for three full turns of 360° without the aircraft entering any dangerous flight attitude during the maneuver. Test must be conducted at minimum flight weight, with minimum of in-flight turbulence. The demonstrated turn rate shall not be less than 12°/s (30 s for a 360° turn) in either direction. 

 Conditions:

Comments:

(1) Lateral Stability – straight and level flight was demonstrated for 2 minutes at minimum   of 1300 lbs in neutral, unaccelorated flight. ( video).
 
(2) Directional stability – At minimum flight weight (1295 lbs me as PIC 185 lbs and 1 hour of fuel 30 lbs). Beginning at 1,500 AGL three full 360’s were completed Left at 40-degree bank angles (at 20
 degrees per second). At 1,000 AGL three full 360’s were completed Right at 40-degree bank angles (at 20 degrees per second). The aircraft did not enter into any dangerous flight altitudes during the maneuvers. (video #2)