Fig. 1 ( a ) Schematic of a NACA 12 airfoil profile used in the model with air speed demarked as U ∞ and the definition of x and y distances. Also illustrated is the chord length ( l s ) used to define the aircraft wing length, ( b ) exploded view (dotted box in ( a )) of the a... More about this image found in ( a ) Schematic of a NACA 12 airfoil profile used in the model with air spe...

Fig. 2 Flowchart of the model algorithm implemented in matlab and used to calculate the pulse deicing power requirement for the various parameters defined in Table 1 . The matlab code is included as Supplemental Materials on the ASME Digital Collection. More about this image found in Flowchart of the model algorithm implemented in matlab and used to calcul...

Fig. 3 Local skin friction coefficient ( C f , x ) as a function of chord position ( x ) for the top and bottom surfaces of a NACA 12 airfoil. Results were determined using xfoil software. Inset: cross-sectional profile of the NACA 12 airfoil depicting the local boundary layer... More about this image found in Local skin friction coefficient ( C f , x ) as a function of...

Fig. 4 ( a ) and ( b ) Local temperature ( T ( y ,   t ) ) as a function of location ( y ) for various time-steps until complete deicing is achieved, for ( a ) t s  = 10 mm, t i  = 1 mm, and t h  = 0.05 mm, ( b ) t s  = 10 mm, ... More about this image found in ( a ) and ( b ) Local temperature ( T ( y ,   t ) ) as a function...

Fig. 5 Power required ( P , left axis) and heat flux ( q ″ , right axis) by a Boeing-747 scale aircraft ( A  = 16 m 2 ) as a function of pulse time ( Δ t pulse ) for ( a ) a subset of heater thermal conductivities ( k h ) having a heater thickness of t h ... More about this image found in Power required ( P , left axis) and heat flux ( q ″ , right axis...

Fig. 6 ( a ) Power ( P ) and ( b ) energy ( E ) required to achieve complete deicing as a function of pulse time ( Δ t pulse ) for a variety of air speeds ( U rel = U ∞ ) and aircraft length scales. Aircraft considered are Cessna ( A  = 1 m 2 ), Em... More about this image found in ( a ) Power ( P ) and ( b ) energy ( E ) required to achieve comple...

Fig. 7 Maximum insulator temperature ( T i , max ) during the pulse deicing cycle as a function of insulator thickness ( t i ) for a variety of insulator thermal conductivities ( k i ) on a ( a ) Cessna-172, ( b ) Embraer-175, and ( c ) Boeing-747 aircraft ... More about this image found in Maximum insulator temperature ( T i , max ) during the pulse...

Fig. 8 Aircraft pulse deicing circuit schematic for ( a ) in-flight deicing using electric power from the aircraft generator and on-board electrical storage (battery), ( b ) in-flight deicing using supercapacitors that are charged every time the flight is on ground, and ( c ) on-ground deicing wit... More about this image found in Aircraft pulse deicing circuit schematic for ( a ) in-flight deicing using ...

Fig. 9 Mass ( m ) as a function of required pulse power ( P ) for a variety of energy storage devices. Approximate minimum power requirement for the Cessna-172 ( ≈ 10 kW), Embraer-175 ( ≈ 50 kW), and Boeing-747 ( ≈ 350 kW) scale aircraft are available in the power and energy re... More about this image found in Mass ( m ) as a function of required pulse power ( P ) for a variet...

Fig. 10 Comparison between steady and pulse deicing techniques: ( a ) Minimum pulse time ( Δ t pulse ) required to achieve deicing of a Boeing-747 wing as a function of ice thickness ( t ice ), assuming two constant powers of 1000 kW and 100 kW representing characteristi... More about this image found in Comparison between steady and pulse deicing techniques: ( a ) Minimum pulse...