Estimated Propeller Thrust at Standard Conditions

Estimated Propeller Thrust at Standard Conditions
Weight of UAV W =		grams
Weight of UAV W =		kg
Weight of UAV W =		N
Weight of UAV W =		lbs.
Prop. diameter D =		in
Prop. diameter D =		m
Prop. Pitch =		inch/rev
Number of motors / props =		#
Motor
Motor Kv =		rpm/v
motor volts applied =		volts
Max. Current per motor =		ampere
Max. Motor speed =		rpm
Motor Output Power
constant k =
power =		W
Ampere rating
Battery ampere hour =		amps/hr
Discharge rate max =		amp
Ampere rating =		amp
Max. motor Wattage
Max wattage =		W
Estimated Static thrust
air density ρ =		kg/m³
Motor efficiency =		%
Fluid drag coefficient at max rpm D_c =	0.850	-
Max. Static thrust =		N
Max. Static thrust =		kgf
Max. Static thrust =		lbs.
UAV Maximum thrust =		N
UAV Maximum thrust =		kg
UAV Maximum thrust =		lbs.
Thrust/mass ratio at Max. Thrust =		thrust/mass

Estimated rpm vs thrust table (typically not linear)	% rpm	thrust N