Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Maiarutselvan V
PSG College of Technology (PSGCT), Coimbatore
Maiarutselvan V has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag in an accelerated flight
Drag Force=(Thrust of an aircraft*cos(Thrust angle))-(Mass*[g]*(sin(Flight path angle)))-(Mass*Acceleration) GO
Weight of aircraft for given coefficients of lift and drag
Weight=lift coefficient*Thrust of an aircraft/Drag Coefficient GO
Coefficient of Drag for given thrust and weight
Drag Coefficient=Thrust of an aircraft*lift coefficient/Weight GO
Coefficient of Lift for given thrust and weight
lift coefficient=Weight*Drag Coefficient/Thrust of an aircraft GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Lift for an unaccelerated flight
Lift force=Weight-(Thrust of an aircraft*sin(Thrust angle)) GO
Thrust angle for an unaccelerated flight for given lift
Thrust angle=asin((Weight-Lift force)/Thrust of an aircraft) GO
Weight of aircraft in level, unaccelerated flight
Weight=Lift force+(Thrust of an aircraft*sin(Thrust angle)) GO
Drag for a level, unaccelerated flight
Drag Force=Thrust of an aircraft*(cos(Thrust angle)) GO
Weight of aircraft for given Lift-to-drag ratio
Weight=Thrust of an aircraft*Lift-to-drag ratio GO
Thrust required for given Lift-to-drag ratio
Thrust of an aircraft=Weight/Lift-to-drag ratio GO

3 Other formulas that calculate the same Output

Lift-to-Drag ratio for given Range of Propeller-Driven Airplane
Lift-to-drag ratio=Specific Fuel Consumption*Range of aircraft/(Propeller efficiency*ln(Gross Weight/Weight without fuel)) GO
Lift-to-Drag ratio for given Endurance of Jet Airplane
Lift-to-drag ratio=Thrust-Specific Fuel Consumption*Endurance of aircraft/(ln(Gross Weight/Weight without fuel)) GO
Lift-to-drag ratio for given glide angle
Lift-to-drag ratio=1/tan(Glide angle) GO

Lift-to-drag ratio for given required thrust Formula

Lift-to-drag ratio=Weight/Thrust of an aircraft
L/D=W/T
More formulas
Drag Coefficient for given parasite drag coefficient GO
Drag Coefficient for given zero-lift drag coefficient GO
Coefficient of Drag due to lift GO
Parasite Drag Coefficient at zero lift GO
Thrust in an accelerated flight GO
Drag in an accelerated flight GO
Lift in an accelerated flight GO
Centrifugal Force in an accelerated flight GO
Velocity in an accelerated flight GO
Thrust for a level, unaccelerated flight GO
Drag for a level, unaccelerated flight GO
Thrust angle for an unaccelerated flight for given drag GO
Lift for an unaccelerated flight GO
Weight of aircraft in level, unaccelerated flight GO
Thrust angle for an unaccelerated flight for given lift GO
Thrust required for level, unaccelerated flight GO
Drag for a level, unaccelerated flight at negligible thrust angle GO
Lift for a level, unaccelerated flight at negligible thrust angle GO
Weight of aircraft for a level, unaccelerated flight at negligible thrust angle GO
Thrust-to-weight ratio GO
Thrust for given coefficients of lift and drag GO
Weight of aircraft for given coefficients of lift and drag GO
Coefficient of Drag for given thrust-to-weight ratio GO
Coefficient of Lift for given thrust-to-weight ratio GO
Coefficient of Drag for given thrust and weight GO
Coefficient of Lift for given thrust and weight GO
Thrust required for given Lift-to-drag ratio GO
Weight of aircraft for given Lift-to-drag ratio GO
Minimum Thrust required GO
Zero-lift drag coefficient for given required thrust GO
Lift-induced drag coefficient for given required thrust GO
Minimum Thrust required for given lift coefficient GO
Zero-lift drag coefficient for given lift coefficient GO
Lift coefficient for given minimum required thrust GO
Minimum Thrust required for given weight GO
Zero-lift drag coefficient at minimum required thrust GO
Power required for given required thrust GO
Thrust required for given required power GO
Freestream velocity for given required power GO
Power required for given aerodynamic coefficients GO
Weight of aircraft for given required power GO
Zero-lift drag coefficient for minimum power required GO
Coefficient of Drag due to lift for minimum power required GO
Power required for given total drag GO
Total drag for given required power GO
Freestream Velocity for given total drag GO
Power available for reciprocating engine-propeller combination GO
Shaft brake power for reciprocating engine-propeller combination GO
Propeller efficiency for reciprocating engine-propeller combination GO
Rate of Climb GO
Velocity of aircraft at a given rate of climb GO
Flight path angle at a given rate of climb GO
Velocity at sea-level condition GO
Power required at sea-level condition GO
Velocity at an altitude GO
Power required at an altitude GO
Velocity at an altitude for given velocity at sea-level condition GO
Power required at an altitude for given power required at sea-level condition GO
Excess power GO
Thrust available for given excess power GO
Total Drag for given excess power GO
Velocity of aircraft for given excess power GO
Rate of Climb for given excess power GO
Excess power for given rate of climb GO
Weight of aircraft for given excess power GO
Glide angle GO
Glide angle for given lift-to-drag ratio GO
Lift-to-drag ratio for given glide angle GO
Lift for given glide angle GO
Drag for given glide angle GO
Range of Propeller-Driven Airplane GO
Propeller Efficiency for given Range of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Range of Propeller-Driven Airplane GO
Range of Propeller-Driven Airplane for given lift-to-drag ratio GO
Propeller Efficiency for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Range and lift-to-drag ratio of Propeller-Driven Airplane GO
Lift-to-Drag ratio for given Range of Propeller-Driven Airplane GO
Endurance of Propeller-Driven Airplane GO
Propeller Efficiency for given Endurance of Propeller-Driven Airplane GO
Specific Fuel Consumption for given Endurance of Propeller-Driven Airplane GO
Endurance of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance of Jet Airplane GO
Endurance for given Lift-to-Drag ratio of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Endurance and Lift-to-Drag ratio of Jet Airplane GO
Lift-to-Drag ratio for given Endurance of Jet Airplane GO
Range of Jet Airplane GO
Thrust-Specific Fuel Consumption for given Range of Jet Airplane GO
Resistance force during ground roll GO
Coefficient of rolling friction during ground roll GO
Weight of aircraft during ground roll GO
Lift acting on aircraft during ground roll GO
Ground effect factor GO
Drag during ground effect GO
Liftoff velocity for given stall velocity GO
Stall velocity for given liftoff velocity GO
Liftoff velocity for given weight GO
Stall velocity for given weight GO
Maximum Lift coefficient for given stall velocity GO
Maximum Lift coefficient for given liftoff velocity GO
Liftoff distance GO
Thrust for given liftoff distance GO
Lift during level turn GO
Bank angle during level turn GO
Weight during level turn GO
Load factor GO
Landing ground roll distance using thrust reversal GO
Touchdown velocity GO
Touchdown velocity for given stall velocity GO
Stall velocity for given touchdown velocity GO
Landing ground roll distance GO
Lift for a given load factor GO
Weight for a given load factor GO
Turn radius GO
Velocity for a given turn radius GO
Load factor for a given turn radius GO
Turn rate GO
Velocity for a given turn rate GO
Load factor for a given turn rate GO
Pull-up maneuver radius GO
Velocity for a given pull-up maneuver radius GO
Load factor for a given pull-up maneuver radius GO
Pull-up maneuver rate GO
Load factor for a given pull-up maneuver rate GO
Velocity for a given pull-up maneuver rate GO
Pull-down maneuver radius GO
Velocity for a given pull-down maneuver radius GO
Load factor for a given pull-down maneuver radius GO
Pull-down maneuver rate GO
Velocity for a given pull-down maneuver rate GO
Load factor for a given pull-down maneuver rate GO
Turn radius for a high load factor GO
Velocity for a given turn radius for a high load factor GO
Load factor for a given turn radius for a high-performance fighter aircraft GO
Turn rate for a high load factor GO
Velocity for a given turn rate for a high load factor GO
Load factor for a given turn rate for a high-performance fighter aircraft GO
Radius of turn for a given lift coefficient GO
Lift Coefficient for a given turn radius GO
Turn rate for a given lift coefficient GO
Lift Coefficient for a given turn rate GO
Radius of turn for a given wing loading GO
Lift Coefficient for a given wing loading and turn radius GO
Wing loading for a given turn radius GO
Turn rate for a given wing loading GO
Wing loading for a given turn rate GO

How to determine the lift-to-drag ratio?

The Lift-to-drag ratio for an aircraft can be determined by flight test, by calculation, or by testing in a wind tunnel.

How to Calculate Lift-to-drag ratio for given required thrust?

Lift-to-drag ratio for given required thrust calculator uses Lift-to-drag ratio=Weight/Thrust of an aircraft to calculate the Lift-to-drag ratio, The Lift-to-drag ratio for given required thrust in a steady, level flight is given by the weight divided by the required thrust of an aircraft. Lift-to-drag ratio and is denoted by L/D symbol.

How to calculate Lift-to-drag ratio for given required thrust using this online calculator? To use this online calculator for Lift-to-drag ratio for given required thrust, enter Weight (W) and Thrust of an aircraft (T) and hit the calculate button. Here is how the Lift-to-drag ratio for given required thrust calculation can be explained with given input values -> 1 = 100/100.

FAQ

What is Lift-to-drag ratio for given required thrust?
The Lift-to-drag ratio for given required thrust in a steady, level flight is given by the weight divided by the required thrust of an aircraft and is represented as L/D=W/T or Lift-to-drag ratio=Weight/Thrust of an aircraft. Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass and The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
How to calculate Lift-to-drag ratio for given required thrust?
The Lift-to-drag ratio for given required thrust in a steady, level flight is given by the weight divided by the required thrust of an aircraft is calculated using Lift-to-drag ratio=Weight/Thrust of an aircraft. To calculate Lift-to-drag ratio for given required thrust, you need Weight (W) and Thrust of an aircraft (T). With our tool, you need to enter the respective value for Weight and Thrust of an aircraft and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Lift-to-drag ratio?
In this formula, Lift-to-drag ratio uses Weight and Thrust of an aircraft. We can use 3 other way(s) to calculate the same, which is/are as follows -
  • Lift-to-drag ratio=1/tan(Glide angle)
  • Lift-to-drag ratio=Specific Fuel Consumption*Range of aircraft/(Propeller efficiency*ln(Gross Weight/Weight without fuel))
  • Lift-to-drag ratio=Thrust-Specific Fuel Consumption*Endurance of aircraft/(ln(Gross Weight/Weight without fuel))
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