Our heavyweight helicopter equal in the world does not have
In Rostov started production of the most load-lifting rotary-wing car The Russian holding «Helicopt[...]
Special Recent Posts
In Italy broke experimental tiltrotor
The experimental military man конвертоплан, developed by "August Vestland's" company, brok[...]
The old plane — nonsense, pilots think - there was an attack
In spite of the fact that the main version of crash of the Russian plane of the Kogalymavia company [...]
The Israeli Apache will subject to peeling
The Israeli shock Boeing AH-64 Apache helicopters will undergo "peeling" procedure. As rep[...]
The aviation industry began to move
On Monday against Dubai Airshow air show - the 2015th Deputy Prime Minister Dmitry Rogozin blew up t[...]
Sitemap
Posts
- Category: Helicopter Test and Evaluation (continued)
- The lateral/directional oscillation (Dutch roll mode)
- Dynamic stability in the hover
- Control derivatives
- LATERAL/DIRECTIONAL DYNAMIC STABILITY AND CONTROL RESPONSE
- Other contributions to Lv
- Lateral (rolling) static stability
- Fuselage contribution to Nv
- Fin contribution to Nv
- Directional (yawing) static stability
- LATERAL/DIRECTIONAL STATIC STABILITY
- Effect of change in speed stability
- Effect of aero-derivatives on dynamic stability modes
- Short-term or pitch (subsidence) mode
- Dynamic stability in the hover
- Longitudinal motion of the helicopter
- Collective pitch derivatives
- Vertical velocity derivatives
- LONGITUDINAL DYNAMIC STABILITY AND CONTROL RESPONSE
- 4.8 MANOEUVRE STABILITY
- Climbing and descending flight
- LONGITUDINAL STATIC STABILITY
- Rotor flapping and disk tilt
- ROTOR CONTRIBUTIONS TO STATIC AND DYNAMIC STABILITY. Changes to blade lift
- Semi-rigid rotors
- Variation of control power with hinge offset
- Flapping motion due to steady pitch or roll rate
- Flapping motion due to cyclic feathering
- Disturbed flapping motion at a constant feather angle
- Pure lead/lag motion
- EQUATIONS OF FLAPPING MOTION
- EQUATIONS OF MOTION FOR A RIGID AIRFRAME
- Normalized and non-dimensional derivatives
- Derivation of aerodynamic derivatives
- AERO-DERIVATIVES FOR ROTORCRAFT
- Stability and Control Theory
- DETERMINATION OF PERFORMANCE LIMITED PARAMETERS
- Ceiling climb tests
- Measuring climb performance
- Estimating the climb performance
- Analysis of a climbing helicopter using momentum theory
- One-engine inoperative testing
- Vertical climbs
- Tethered hovering
- Ground-referenced hovering
- Free-air hovering
- General test conditions and methodology
- Vertical climb testing
- Developing a test philosophy using the free-air method
- Tip effects evaluation
- VERTICAL PERFORMANCE TESTING
- Planning a level flight performance trial
- Flight test techniques
- General test conditions
- Choice of referred grouping
- Reduction of level flight performance data
- Effects of variable specific fuel consumption
- Endurance performance
- Flying at best range speed
- Factors affecting range performance
- Range performance
- Choice of suitable test site(s)
- The Wlam1 method
- The W/8 method
- Control of the referred groups
- Derivation of the referred parameter relationships
- NON-DIMENSIONAL PARAMETERS
- Performance Testing
- High hover height
- The knee point
- Lower hover height
- THE AVOID CURVE
- Estimating the minimum touchdown speed
- The flare, the check and the level manoeuvre
- Speeds for maximum range and endurance
- AUTOROTATIVE PERFORMANCE
- Windmilling rotors and autorotation
- Delay time
- Pilot action and rate of descent
- Factors affecting rotor speed decay
- AUTOROTATION
- Incipient vortex-ring condition
- Improved predictions
- Predicting vortex-ring boundaries using dynamic inflow methods
- Tail rotor stall
- Power required by the tail rotor in the hover
- TAIL ROTOR POWER
- Main rotor power
- Blade stall and drag divergence
- Non-uniform inflow
- Reversed flow
- HORIZONTAL FLIGHT: IMPROVED THEORETICAL ESTIMATES
- Rotor profile power
- HORIZONTAL FLIGHT: BLADE ELEMENT THEORY
- Estimating the induced velocity
- Elliptically loaded wing analogy
- The windmill-brake state
- The vortex-ring state
- AXIAL FLIGHT: VERTICAL DESCENTS AND THE VORTEX-RING STATE
- Ground effect
- Fuselage download