Gross weight given drag Solution

STEP 0: Pre-Calculation Summary
Formula Used
Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient)
W0 = FD*(CL/CD)
This formula uses 4 Variables
Variables Used
Gross Weight - (Measured in Kilogram) - The Gross Weight of the airplane is the weight with full fuel and payload.
Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
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.
Drag Coefficient - Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
STEP 1: Convert Input(s) to Base Unit
Drag Force: 80 Newton --> 80 Newton No Conversion Required
Lift Coefficient: 1.1 --> No Conversion Required
Drag Coefficient: 1.5 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
W0 = FD*(CL/CD) --> 80*(1.1/1.5)
Evaluating ... ...
W0 = 58.6666666666667
STEP 3: Convert Result to Output's Unit
58.6666666666667 Kilogram --> No Conversion Required
FINAL ANSWER
58.6666666666667 58.66667 Kilogram <-- Gross Weight
(Calculation completed in 00.020 seconds)

Credits

Created by Himanshu Sharma
National Institute of Technology, Hamirpur (NITH), Himachal Pradesh
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13 Aerodynamic Design Calculators

Aerofoil Thickness for 4 Digit Series
Go Half Thickness = (Maximum Thickness* (0.2969*Position Along the chord^0.5- 0.1260*Position Along the chord- 0.3516*Position Along the chord^2+ 0.2843*Position Along the chord^3- 0.1015*Position Along the chord^4))/0.2
Thrust-to-Weight Ratio given Minimum Coefficient of Drag
Go Thrust-to-Weight Ratio = (Minimum Drag Coefficient/Wing Loading+Lift Induced Drag Constant*(Load Factor/Dynamic Pressure)^2*Wing Loading)*Dynamic Pressure
Span given Induced Drag
Go Lateral Plane Span = Lift Force/sqrt(pi*Induced Drag*Dynamic Pressure)
Form Factor given Flat Plate Area
Go Form Factor Drag = (Flat Plate Area)/(Skin Friction Coefficient*Aircraft Wetted Area)
Skin Friction Coefficient given Flat Plate Area
Go Skin Friction Coefficient = Flat Plate Area/(Form Factor Drag*Aircraft Wetted Area)
Wetted Area given Flat Plate Area
Go Aircraft Wetted Area = Flat Plate Area/(Form Factor Drag*Skin Friction Coefficient)
Equivalent Parasite Drag Area
Go Flat Plate Area = Form Factor Drag*Skin Friction Coefficient*Aircraft Wetted Area
Span given Aspect Ratio
Go Lateral Plane Span = sqrt(Aspect Ratio in Lateral Plane*Aircraft Wetted Area)
Gross weight given drag
Go Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient)
Wetted Area given Aspect Ratio
Go Aircraft Wetted Area = Lateral Plane Span^2/Aspect Ratio in Lateral Plane
Aspect Ratio of Wing
Go Aspect Ratio in Lateral Plane = Lateral Plane Span^2/Aircraft Wetted Area
Taper Ratio of Airfoil
Go Taper Ratio = Tip Chord Length/Root Chord Length
Tip Speed Ratio with Blade Number
Go Tip Speed Ratio = (4*pi)/Number of Blades

Gross weight given drag Formula

Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient)
W0 = FD*(CL/CD)

What is gross weight?

The gross weight is the total weight of the goods carried, including all packaging but excluding the tare weight of the transport unit. The tare weight is the weight of a transport unit before any cargo is loaded.

How to Calculate Gross weight given drag?

Gross weight given drag calculator uses Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient) to calculate the Gross Weight, The Gross weight given drag formula is defined as the total weight of the aircraft at the time of stage of drag force on aircraft. Gross Weight is denoted by W0 symbol.

How to calculate Gross weight given drag using this online calculator? To use this online calculator for Gross weight given drag, enter Drag Force (FD), Lift Coefficient (CL) & Drag Coefficient (CD) and hit the calculate button. Here is how the Gross weight given drag calculation can be explained with given input values -> 58.66667 = 80*(1.1/1.5).

FAQ

What is Gross weight given drag?
The Gross weight given drag formula is defined as the total weight of the aircraft at the time of stage of drag force on aircraft and is represented as W0 = FD*(CL/CD) or Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient). Drag Force is the resisting force experienced by an object moving through a fluid, 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 & Drag Coefficient is a dimensionless quantity that is used to quantify the drag or resistance of an object in a fluid environment, such as air or water.
How to calculate Gross weight given drag?
The Gross weight given drag formula is defined as the total weight of the aircraft at the time of stage of drag force on aircraft is calculated using Gross Weight = Drag Force*(Lift Coefficient/Drag Coefficient). To calculate Gross weight given drag, you need Drag Force (FD), Lift Coefficient (CL) & Drag Coefficient (CD). With our tool, you need to enter the respective value for Drag Force, Lift Coefficient & Drag Coefficient and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
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