Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Sai Venkata Phanindra Chary Arendra
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 100+ more calculators!

11 Other formulas that you can solve using the same Inputs

Diagonal of a Rectangle when breadth and area are given
Diagonal=sqrt(((Area)^2/(Breadth)^2)+(Breadth)^2) GO
Diagonal of a Rectangle when length and area are given
Diagonal=sqrt(((Area)^2/(Length)^2)+(Length)^2) GO
Side of a Kite when other side and area are given
Side A=(Area*cosec(Angle Between Sides))/Side B GO
Perimeter of rectangle when area and rectangle length are given
Perimeter=(2*Area+2*(Length)^2)/Length GO
Buoyant Force
Buoyant Force=Pressure*Area GO
Perimeter of a square when area is given
Perimeter=4*sqrt(Area) GO
Diagonal of a Square when area is given
Diagonal=sqrt(2*Area) GO
Length of rectangle when area and breadth are given
Length=Area/Breadth GO
Breadth of rectangle when area and length are given
Breadth=Area/Length GO
Pressure when force and area are given
Pressure=Force/Area GO
Stress
Stress=Force/Area GO

9 Other formulas that calculate the same Output

Minimum Thrust required for given weight
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)) GO
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
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 Formula

Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift)
T=P<sub>dynamic*A*(C<sub>D,0</sub>+C<sub>D,i</sub>)
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 for given lift coefficient GO
Lift coefficient for given minimum required thrust GO
Minimum Thrust required for given weight GO

In a passenger airplane, how much thrust is required?

In a passenger airplane, at least enough thrust is required to keep the airplane flying at the speed of minimum drag.

How to Calculate Minimum Thrust required?

Minimum Thrust required calculator uses Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift) to calculate the Thrust of an aircraft, The Minimum Thrust required for a steady, level flight is equal to the sum of drag due to zero lift and drag due to lift. Thrust of an aircraft and is denoted by T symbol.

How to calculate Minimum Thrust required using this online calculator? To use this online calculator for Minimum Thrust required, enter Dynamic Pressure (Pdynamic), Area (A), Zero-lift drag coefficient (CD,0) and Coefficient of drag due to lift (CD,i) and hit the calculate button. Here is how the Minimum Thrust required calculation can be explained with given input values -> 408.05 = 10*50*(0.0161+0.8).

FAQ

What is Minimum Thrust required?
The Minimum Thrust required for a steady, level flight is equal to the sum of drag due to zero lift and drag due to lift and is represented as T=Pdynamic*A*(CD,0+CD,i) or Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift). 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 area is the amount of two-dimensional space taken up by an object, 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 and The Coefficient of drag due to lift is the sum of the coefficients of induced drag and the increment in parasite drag due to the angle of attack different from the zero-lift angle of attack.
How to calculate Minimum Thrust required?
The Minimum Thrust required for a steady, level flight is equal to the sum of drag due to zero lift and drag due to lift is calculated using Thrust of an aircraft=Dynamic Pressure*Area*(Zero-lift drag coefficient+Coefficient of drag due to lift). To calculate Minimum Thrust required, you need Dynamic Pressure (Pdynamic), Area (A), Zero-lift drag coefficient (CD,0) and Coefficient of drag due to lift (CD,i). With our tool, you need to enter the respective value for Dynamic Pressure, Area, Zero-lift drag coefficient and Coefficient of drag due to lift 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, Area, Zero-lift drag coefficient and Coefficient of drag due to lift. 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+((lift coefficient^2)/(pi*Oswald efficiency factor*Aspect Ratio of a wing)))
  • 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))
  • 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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