Weight of aircraft for level, unaccelerated flight at negligible thrust angle Solution

STEP 0: Pre-Calculation Summary
Formula Used
Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Wbody = Pdynamic*A*CL
This formula uses 4 Variables
Variables Used
Weight of Body - (Measured in Newton) - Weight of Body is the force acting on the object due to gravity.
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.
Lift Coefficient - The Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
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
Lift Coefficient: 1.1 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Wbody = Pdynamic*A*CL --> 10*20*1.1
Evaluating ... ...
Wbody = 220
STEP 3: Convert Result to Output's Unit
220 Newton --> No Conversion Required
FINAL ANSWER
220 Newton <-- Weight of Body
(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!
Vallurupalli Nageswara Rao Vignana Jyothi Institute of Engineering and Technology (VNRVJIET), Hyderabad
Sai Venkata Phanindra Chary Arendra has verified this Calculator and 300+ 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

Weight of aircraft for level, unaccelerated flight at negligible thrust angle Formula

Weight of Body = Dynamic Pressure*Area*Lift Coefficient
Wbody = Pdynamic*A*CL

What is the most aerodynamic shape?

For speeds lower than the speed of sound, the most aerodynamically efficient shape found is the teardrop.

How to Calculate Weight of aircraft for level, unaccelerated flight at negligible thrust angle?

Weight of aircraft for level, unaccelerated flight at negligible thrust angle calculator uses Weight of Body = Dynamic Pressure*Area*Lift Coefficient to calculate the Weight of Body, The Weight of aircraft for level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift. Weight of Body is denoted by Wbody symbol.

How to calculate Weight of aircraft for level, unaccelerated flight at negligible thrust angle using this online calculator? To use this online calculator for Weight of aircraft for level, unaccelerated flight at negligible thrust angle, enter Dynamic Pressure (Pdynamic), Area (A) & Lift Coefficient (CL) and hit the calculate button. Here is how the Weight of aircraft for level, unaccelerated flight at negligible thrust angle calculation can be explained with given input values -> 88 = 10*20*1.1.

FAQ

What is Weight of aircraft for level, unaccelerated flight at negligible thrust angle?
The Weight of aircraft for level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift and is represented as Wbody = Pdynamic*A*CL or Weight of Body = Dynamic Pressure*Area*Lift Coefficient. 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 Lift Coefficient is a dimensionless coefficient that relates the lift generated by a lifting body to the fluid density around the body, the fluid velocity and an associated reference area.
How to calculate Weight of aircraft for level, unaccelerated flight at negligible thrust angle?
The Weight of aircraft for level, unaccelerated flight at negligible thrust angle is the product of dynamic pressure, reference area, and coefficient of lift is calculated using Weight of Body = Dynamic Pressure*Area*Lift Coefficient. To calculate Weight of aircraft for level, unaccelerated flight at negligible thrust angle, you need Dynamic Pressure (Pdynamic), Area (A) & Lift Coefficient (CL). With our tool, you need to enter the respective value for Dynamic Pressure, Area & Lift Coefficient 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 Weight of Body?
In this formula, Weight of Body uses Dynamic Pressure, Area & Lift Coefficient. We can use 4 other way(s) to calculate the same, which is/are as follows -
  • Weight of Body = Lift Force+(Thrust*sin(Thrust angle))
  • Weight of Body = Lift Coefficient*Thrust/Drag Coefficient
  • Weight of Body = Thrust*Lift-to-drag Ratio
  • Weight of Body = Power*Lift Coefficient/(Freestream Velocity*Drag Coefficient)
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