FIELD: aviation.
SUBSTANCE: method includes blowing of blade section model with regularly pulsating flow, periodic variation of angle of attack of the model, in this case control of selectors of flow rate pulsation frequency and pulsation frequency of angle of attack of the model is carried out by means of phase shifter, the control signal for which is generated during the experiment in aerodynamic tunnel on the basis of measurements of flow rate and angle of attack of the model.
EFFECT: improving the modelling quality during tests.
1 dwg
| Title | Year | Author | Number |
|---|---|---|---|
| WIND-TUNNEL | 2013 |
|
RU2526515C1 |
| METHOD OF DETERMINING AERODYNAMIC DAMPING CHARACTERISTICS OF PROPELLER AEROPLANES AND METHOD TO THIS END | 2009 |
|
RU2402005C1 |
| METHOD OF DEFINING FACTORS OF AERODYNAMIC FORCES AND MOMENTS AT STEADY-STATE ROTATION OF AIRCRAFT MODEL AND DEVICE TO THIS END | 2011 |
|
RU2477460C1 |
| HELICOPTER ROTOR BLADE WITH DEFLECTING REAR EDGE | 2015 |
|
RU2603707C1 |
| MEASUREMENT OF PULSATING FLOW PARAMETERS | 2014 |
|
RU2559566C1 |
| METHOD OF DETERMINING DAMPING PROPERTIES OF AEROPLANE MODELS WITH PROPELLERS | 2007 |
|
RU2344397C2 |
| HELICOPTER ROTOR BLADE | 2017 |
|
RU2662591C1 |
| DYNAMICALLY SIMILAR AERODYNAMIC MODEL OF AIRCRAFT BEARING SURFACE | 2014 |
|
RU2578915C1 |
| TEST METHOD IN WIND TUNNELS WITH SIMULATION OF EFFECT OF VERTICAL, HORIZONTAL OR MIXED GUST OF WIND | 2024 |
|
RU2827746C1 |
| METHOD OF DETERMINATION OF THE CONTROL SIGNAL ON THE CORNER OF THE ROLL MODEL OF THE HYPERPOWER VEHICLE EQUIPMENT (HVE) FOR MONITORING THE AERODYNAMIC IDENTITY ON THE REINOLDS NUMBER OF TRAJECTORIES OF THE FLIGHT OF THE MODEL AND THE NUCLEAR ARTICLE WHEN CONDUCTING ANTI-STATE AIRCRAFT RESEARCH | 2016 |
|
RU2615220C1 |
