Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

11 Other formulas that you can solve using the same Inputs

Drag Coefficient for given parasite drag coefficient
Drag Coefficient=Parasite Drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)) GO
Non-dimensional pressure coefficient
Pressure coefficient=Change in static pressure/Dynamic Pressure GO
Moment coefficient
moment coefficient=moment/(Dynamic Pressure*Area*Chord Length) GO
Normal Force Coefficient
coefficient of force=Normal Force/(Dynamic Pressure*Area) GO
Velocity of Fluid When Dynamic Pressure is Given
Fluid Velocity=sqrt(Dynamic Pressure*2/Liquid Density) GO
Density of the Liquid When Dynamic Pressure is Given
Liquid Density=2*Dynamic Pressure/(Fluid Velocity^2) GO
Coefficient of drag
Drag Coefficient=Drag Force/(Dynamic Pressure*Area) GO
lift coefficient
lift coefficient=Lift force/(Dynamic Pressure*Area) GO
Axial force coefficient
coefficient of force=Force/(Dynamic Pressure*Area) GO
Lift Force
Lift force=lift coefficient*Dynamic Pressure*Area GO
Drag force
Drag Force=Drag Coefficient*Dynamic Pressure*Area GO

9 Other formulas that calculate the same Output

Minimum Thrust required for given lift coefficient
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing))) GO
Thrust for given liftoff distance
Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance) GO
Thrust in an accelerated flight
Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration)) GO
Minimum Thrust required
Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) GO
Thrust for given coefficients of lift and drag
Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient GO
Thrust required for level, unaccelerated flight
Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient GO
Thrust for a level, unaccelerated flight
Thrust of an aircraft=Drag Force/(cos(Thrust angle)) GO
Thrust required for given Lift-to-drag ratio
Thrust of an aircraft=Weight/Lift-to-drag ratio GO
Thrust required for given required power
Thrust of an aircraft=Power/Freestream Velocity GO

Minimum Thrust required for given weight Formula

Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing))
T=(P<sub>dynamic*S*C<sub>D,0</sub>)+((W^2)/(P<sub>dynamic*S*pi*e*AR))
More formulas
Thrust required for level, unaccelerated flight 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 Lift for given thrust-to-weight ratio GO
Coefficient of Lift for given thrust and weight GO
Minimum Thrust required GO
Minimum Thrust required for given lift coefficient GO
Lift coefficient for given minimum required thrust GO

What is maximum takeoff weight?

Maximum takeoff weight (MTOW) is the maximum weight at which the pilot of the aircraft is allowed to attempt to take off.

How to Calculate Minimum Thrust required for given weight?

Minimum Thrust required for given weight calculator uses Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)) to calculate the Thrust of an aircraft, The Minimum Thrust required for given weight for a steady, level flight is a function of zero-lift drag coefficient, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of an aircraft. Thrust of an aircraft and is denoted by T symbol.

How to calculate Minimum Thrust required for given weight using this online calculator? To use this online calculator for Minimum Thrust required for given weight, enter Dynamic Pressure (Pdynamic), Reference Area (S), Zero-lift drag coefficient (CD,0), Weight (W), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR) and hit the calculate button. Here is how the Minimum Thrust required for given weight calculation can be explained with given input values -> 32.63599 = (10*5*0.0161)+((100^2)/(10*5*pi*0.5*4)).

FAQ

What is Minimum Thrust required for given weight?
The Minimum Thrust required for given weight for a steady, level flight is a function of zero-lift drag coefficient, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of an aircraft and is represented as T=(Pdynamic*S*CD,0)+((W^2)/(Pdynamic*S*pi*e*AR)) or Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)). Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, The Zero-lift drag coefficient is a dimensionless parameter that relates an aircraft's zero-lift drag force to its size, speed, and flying altitude, Weight is a vector quantity and defined as the product of mass and acceleration acting on that mass, The Oswald efficiency factor is a correction factor that represents the change in drag with lift of a three-dimensional wing or airplane, as compared with an ideal wing having the same aspect ratio and The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
How to calculate Minimum Thrust required for given weight?
The Minimum Thrust required for given weight for a steady, level flight is a function of zero-lift drag coefficient, dynamic pressure, reference area, Oswald efficiency factor, and aspect ratio of the wing of an aircraft is calculated using Thrust of an aircraft=(Dynamic Pressure*Reference Area*Zero-lift drag coefficient)+((Weight^2)/(Dynamic Pressure*Reference Area*pi*Oswald efficiency factor*Aspect Ratio of a wing)). To calculate Minimum Thrust required for given weight, you need Dynamic Pressure (Pdynamic), Reference Area (S), Zero-lift drag coefficient (CD,0), Weight (W), Oswald efficiency factor (e) and Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Dynamic Pressure, Reference Area, Zero-lift drag coefficient, Weight, Oswald efficiency factor and Aspect Ratio of a wing 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 Thrust of an aircraft?
In this formula, Thrust of an aircraft uses Dynamic Pressure, Reference Area, Zero-lift drag coefficient, Weight, Oswald efficiency factor and Aspect Ratio of a wing. We can use 9 other way(s) to calculate the same, which is/are as follows -
  • Thrust of an aircraft=(sec(Thrust angle))*(Drag Force+(Mass*[g]*sin(Flight path angle))+(Mass*Acceleration))
  • Thrust of an aircraft=Drag Force/(cos(Thrust angle))
  • Thrust of an aircraft=Dynamic Pressure*Area*Drag Coefficient
  • Thrust of an aircraft=Drag Coefficient*Weight/lift coefficient
  • Thrust of an aircraft=Weight/Lift-to-drag ratio
  • Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift)
  • Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))
  • Thrust of an aircraft=Power/Freestream Velocity
  • Thrust of an aircraft=1.44*(Weight^2)/([g]*Freestream density*Reference Area*Maximum Lift Coefficient*Liftoff Distance)
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