Minimum Thrust required for given weight Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
T = (Pdynamic*A*CD,0)+((Wbody^2)/(Pdynamic*A*pi*e*AR))
This formula uses 1 Constants, 7 Variables
Constants Used
pi - Archimedes' constant Value Taken As 3.14159265358979323846264338327950288
Variables Used
Thrust - (Measured in Newton) - The Thrust of an aircraft is defined as the force generated through propulsion engines that move an aircraft through the air.
Dynamic Pressure - (Measured in Pascal) - Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
Area - (Measured in Square Meter) - The area is the amount of two-dimensional space taken up by an object.
Zero Lift Drag Coefficient - Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift.
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
Oswald Efficiency Factor - 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.
Aspect Ratio of a wing - The Aspect Ratio of a wing is defined as the ratio of its span to its mean chord.
STEP 1: Convert Input(s) to Base Unit
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Area: 20 Square Meter --> 20 Square Meter No Conversion Required
Zero Lift Drag Coefficient: 0.31 --> No Conversion Required
Weight of Body: 221 Newton --> 221 Newton No Conversion Required
Oswald Efficiency Factor: 0.51 --> No Conversion Required
Aspect Ratio of a wing: 4 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T = (Pdynamic*A*CD,0)+((Wbody^2)/(Pdynamic*A*pi*e*AR)) --> (10*20*0.31)+((221^2)/(10*20*pi*0.51*4))
Evaluating ... ...
T = 100.104345958585
STEP 3: Convert Result to Output's Unit
100.104345958585 Newton --> No Conversion Required
FINAL ANSWER
100.104345958585 100.1043 Newton <-- Thrust
(Calculation completed in 00.004 seconds)

Credits

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

19 Thrust and Power Requirements Calculators

Minimum Thrust required for given weight
Go Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
Minimum Thrust required for given lift coefficient
Go Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))
Minimum Thrust of aircraft required
Go Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)
Weight of aircraft for given required power
Go Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)
Power required for given aerodynamic coefficients
Go Power = Weight of Body*Freestream Velocity*Drag Coefficient/Lift Coefficient
Thrust Angle for Unaccelerated Level Flight for given Lift
Go Thrust angle = asin((Weight of Body-Lift Force)/Thrust)
Weight of aircraft in level, unaccelerated flight
Go Weight of Body = Lift Force+(Thrust*sin(Thrust angle))
Weight of aircraft for given coefficients of lift and drag
Go Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
Thrust for given coefficients of lift and drag
Go Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
Weight of aircraft for level, unaccelerated flight at negligible thrust angle
Go Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Thrust of aircraft required for level, unaccelerated flight
Go Thrust = Dynamic Pressure*Area*Drag Coefficient
Thrust for Level and Unaccelerated Flight
Go Thrust = Drag Force/(cos(Thrust angle))
Thrust Angle for Unaccelerated Level Flight for given Drag
Go Thrust angle = acos(Drag Force/Thrust)
Thrust-to-weight ratio
Go Thrust-to-Weight Ratio = Drag Coefficient/Lift Coefficient
Thrust of aircraft required for given Lift-to-drag ratio
Go Thrust = Weight of Body/Lift-to-drag Ratio
Weight of aircraft for given Lift-to-drag ratio
Go Weight of Body = Thrust*Lift-to-drag Ratio
Power required for given total drag force
Go Power = Drag Force*Freestream Velocity
Power required for given required thrust of aircraft
Go Power = Freestream Velocity*Thrust
Thrust of aircraft required for given required power
Go Thrust = Power/Freestream Velocity

Minimum Thrust required for given weight Formula

Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing))
T = (Pdynamic*A*CD,0)+((Wbody^2)/(Pdynamic*A*pi*e*AR))

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 = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing)) to calculate the Thrust, The Minimum Thrust required for given weight for a steady, level flight is the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket. Thrust 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), Area (A), Zero Lift Drag Coefficient (CD,0), Weight of Body (Wbody), Oswald Efficiency Factor (e) & 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 -> 75.70435 = (10*20*0.31)+((221^2)/(10*20*pi*0.51*4)).

FAQ

What is Minimum Thrust required for given weight?
The Minimum Thrust required for given weight for a steady, level flight is the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket and is represented as T = (Pdynamic*A*CD,0)+((Wbody^2)/(Pdynamic*A*pi*e*AR)) or Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*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 area is the amount of two-dimensional space taken up by an object, Zero Lift Drag Coefficient is the coefficient of drag for an aircraft or aerodynamic body when it is producing zero lift, Weight of Body is the force acting on the object due to gravity, 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 & 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 the force that moves an aircraft through the air. Thrust is used to overcome the drag of an airplane, and to overcome the weight of a rocket is calculated using Thrust = (Dynamic Pressure*Area*Zero Lift Drag Coefficient)+((Weight of Body^2)/(Dynamic Pressure*Area*pi*Oswald Efficiency Factor*Aspect Ratio of a wing)). To calculate Minimum Thrust required for given weight, you need Dynamic Pressure (Pdynamic), Area (A), Zero Lift Drag Coefficient (CD,0), Weight of Body (Wbody), Oswald Efficiency Factor (e) & Aspect Ratio of a wing (AR). With our tool, you need to enter the respective value for Dynamic Pressure, Area, Zero Lift Drag Coefficient, Weight of Body, Oswald Efficiency Factor & 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?
In this formula, Thrust uses Dynamic Pressure, Area, Zero Lift Drag Coefficient, Weight of Body, Oswald Efficiency Factor & Aspect Ratio of a wing. We can use 7 other way(s) to calculate the same, which is/are as follows -
  • Thrust = Drag Force/(cos(Thrust angle))
  • Thrust = Dynamic Pressure*Area*Drag Coefficient
  • Thrust = Drag Coefficient*Weight of Body/Lift Coefficient
  • Thrust = Weight of Body/Lift-to-drag Ratio
  • Thrust = Dynamic Pressure*Reference Area*(Zero Lift Drag Coefficient+Coefficient Of Drag Due to Lift)
  • Thrust = Dynamic Pressure*Area*(Zero Lift Drag Coefficient+((Lift Coefficient^2)/(pi*Oswald Efficiency Factor*Aspect Ratio of a wing)))
  • Thrust = Power/Freestream Velocity
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