RC Plane designing

Roopal Raj Sandeep Kr. Mishra Shreya Srivastava 6th B

Introduction :   A

RC R C aircr aircraft aft has all the dynamic chara characteristics cteristics which are present in actual aircraft.  RC Aircrafts can be used to carry some mass of small value or also use by defense authority authorit y by applying a spy camera on it. it. aircraft are also used by research  RC aircraft and development department departmen t in order to check the th e feasibility of any design.

Airfoil: 

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 An airfoil is the 2D 2D cross-section cross-section shape of the wing,  which creates sufficient lift with minimal minimal drag drag..  Types  T ypes::

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Flat bottom airfoil

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Semi-Symmetric airfoil

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Symmetrical airfoil

Terminology

 Airfoil selection:  Wee opted   W

Symmetrical S ymmetrical airfoil because It is use for airplanes having low Mach no. and good stability.

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The selected profile  was “naca0012” .

Lift •

The component of the total aerodynamic force of an airfoil that is perpendicular to the relative wind.

FL = CL ρ A v²/2 Drag •

The component of the total aero  – dynamic force of an airfoil that is parallel to the relative wind.

FD = CD ρ A v²/2

Motion Characteristics

Control Surfaces :  Ailerons:   An aileron

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is a hinged hinged f light contr control ol surface usually attached to the trailing arm of each wing of a fixed-wing aircraft. Movement Mov ement around this th is axis is called 'rolling' or 'banking'.

Rudder: 

The rudder are hinged on rear surface, making as a vertical stabilizer . and its area is half of the whole vertical stabilizer.

Elevators: 

The elevators are hinged on rear surface, making as a whole a tail  plane or horizontal stabilizer .

Stability Concept: Stability may be defined as follows: - Positive stability: tends tend s to return return to original condition after a disturbance. - Negative stability: tends to increase the disturbance. - Neutral stability: remains at the new condition. condition . 

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Dynamic instabilit inst abilityy may be prevented prevented by an even even distribution distribut ion of weight inside the fuselage, avoiding too much weight concentration concentration at a t the extremities extremit ies or at the CG CG..

Neutral point: 

Neutral Point (NP) is the Aerodynamic Centre of the t he whole aircraft.

Centre of pressure: pressure:  

Centre of pressure press ure Cp is a point on the wing where the net lift force assume to be act. The distance of the Cp from leading leadin g edge is at distance of “c/4” unit where “c “c ” is the t he chord length. lengt h.

 Aerodynami  Aer odynamicc cent center(A er(AC): C): 

It is a point on the wing where the net pitching pi tching moment is always constant. constant.

Stability configuration:

Wing Analysis on JAVA Applet:

Calculations:   Wing

area = FL ×2 /CL ×ρ ×V² area

= 10 ×2/0.278 ×1.228 ×10² = 0.188m²   Wing dimensions by taking aspect ratio as 6 = 0.188/1.06 = 0.178m 

Area of horizontal stabilizer stabilizer = wing area/4 = 0.188/4 = 0.94m²

  Area of

vertical stabilizer = Area vertical Area of horizontal stab./2 stab./2 = 0.94/2

= 0.47m²

From given diagram: L = 0.50 × 0.94/(0.188+ 0.94) = 0.42m.

FD = 0.0764 × 0.188 ×10 ×1.228/2 = 0.861 N

CATIA CA TIA Model :

Flow simulation:

Reference: Engine ers”  John J. Bertin “Aerodynamics for Engineers” Fourth Edition U.S Air force Academy.  John D. Anderson “Introduction to f light Dynamics” Third edition.  Wikipedia Softwares used :  JAV VA  A   A pplet -  JA pplet - Flow design - CATIA V 5

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