Drag in Accelerated Flight Calculator

✖Thrust denotes the force exerted by the engine to propel an aircraft forward.ⓘ Thrust [T]			+10% -10%
✖Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.ⓘ Thrust Angle [σ_T]			+10% -10%
✖Mass of Aircraft is the total mass of the plane at any phase of its mission.ⓘ Mass of Aircraft [m]			+10% -10%
✖Flight Path Angle is defined as the angle between horizontal and the flight velocity vector, which describes whether the aircraft is climbing or descending.ⓘ Flight Path Angle [γ]			+10% -10%
✖Acceleration is the rate of change in velocity to the change in time.ⓘ Acceleration [a]			+10% -10%

✖Drag Force is the resisting force experienced by an object moving through a fluid.ⓘ Drag in Accelerated Flight [F_D]

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Drag in Accelerated Flight Solution

STEP 0: Pre-Calculation Summary

Formula Used

Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration
F_D = T*cos(σ_T)-m*[g]*sin(γ)-m*a
This formula uses 1 Constants, 2 Functions, 6 Variables

Constants Used

[g] - Gravitational acceleration on Earth Value Taken As 9.80665

Functions Used

sin - Sine is a trigonometric function that describes the ratio of the length of the opposite side of a right triangle to the length of the hypotenuse., sin(Angle)
cos - Cosine of an angle is the ratio of the side adjacent to the angle to the hypotenuse of the triangle., cos(Angle)

Variables Used

Drag Force - (Measured in Newton) - Drag Force is the resisting force experienced by an object moving through a fluid.
Thrust - (Measured in Newton) - Thrust denotes the force exerted by the engine to propel an aircraft forward.
Thrust Angle - (Measured in Radian) - Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction.
Mass of Aircraft - (Measured in Kilogram) - Mass of Aircraft is the total mass of the plane at any phase of its mission.
Flight Path Angle - (Measured in Radian) - Flight Path Angle is defined as the angle between horizontal and the flight velocity vector, which describes whether the aircraft is climbing or descending.
Acceleration - (Measured in Meter per Square Second) - Acceleration is the rate of change in velocity to the change in time.

STEP 1: Convert Input(s) to Base Unit

Thrust: 700 Newton --> 700 Newton No Conversion Required
Thrust Angle: 0.034 Radian --> 0.034 Radian No Conversion Required
Mass of Aircraft: 20 Kilogram --> 20 Kilogram No Conversion Required
Flight Path Angle: 0.062 Radian --> 0.062 Radian No Conversion Required
Acceleration: 30.37 Meter per Square Second --> 30.37 Meter per Square Second No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

F_D = T*cos(σ_T)-m*[g]*sin(γ)-m*a --> 700*cos(0.034)-20*[g]*sin(0.062)-20*30.37

Evaluating ... ...

F_D = 80.0429821420068

STEP 3: Convert Result to Output's Unit

80.0429821420068 Newton --> No Conversion Required

FINAL ANSWER

80.0429821420068 ≈ 80.04298 Newton <-- Drag Force

(Calculation completed in 00.004 seconds)

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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 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 300+ more calculators!

< Climbing Flight Calculators

Flight path angle at given rate of climb

LaTeX Go Flight Path Angle = asin(Rate of Climb/Velocity)

Velocity of aircraft at given rate of climb

LaTeX Go Velocity = Rate of Climb/sin(Flight Path Angle)

Rate of Climb

LaTeX Go Rate of Climb = Velocity*sin(Flight Path Angle)

Weight of Aircraft for given Excess Power

LaTeX Go Aircraft Weight = Excess Power/Rate of Climb

Drag in Accelerated Flight Formula

LaTeX Go

Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration
F_D = T*cos(σ_T)-m*[g]*sin(γ)-m*a

What is drag in flight?

Drag is the force that resists the movement of an aircraft through the air. There are two basic types: parasite drag and induced drag.

How to Calculate Drag in Accelerated Flight?

Drag in Accelerated Flight calculator uses Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration to calculate the Drag Force, The Drag in Accelerated Flight refers to the aerodynamic force that opposes the motion of an aircraft as it moves through the air, it acts in the direction opposite to the aircraft's velocity vector, this equation appears to calculate the total drag force during climb flight by considering the thrust from the engines, the weight component opposing the flight path, and any additional acceleration experienced by the aircraft. Drag Force is denoted by F_D symbol.

How to calculate Drag in Accelerated Flight using this online calculator? To use this online calculator for Drag in Accelerated Flight, enter Thrust (T), Thrust Angle (σ_T), Mass of Aircraft (m), Flight Path Angle (γ) & Acceleration (a) and hit the calculate button. Here is how the Drag in Accelerated Flight calculation can be explained with given input values -> 80.04298 = 700*cos(0.034)-20*[g]*sin(0.062)-20*30.37.

FAQ

What is Drag in Accelerated Flight?

The Drag in Accelerated Flight refers to the aerodynamic force that opposes the motion of an aircraft as it moves through the air, it acts in the direction opposite to the aircraft's velocity vector, this equation appears to calculate the total drag force during climb flight by considering the thrust from the engines, the weight component opposing the flight path, and any additional acceleration experienced by the aircraft and is represented as F_D = T*cos(σ_T)-m*[g]*sin(γ)-m*a or Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration. Thrust denotes the force exerted by the engine to propel an aircraft forward, Thrust angle is defined as the angle between thrust vector and flight path (or flight velocity) direction, Mass of Aircraft is the total mass of the plane at any phase of its mission, Flight Path Angle is defined as the angle between horizontal and the flight velocity vector, which describes whether the aircraft is climbing or descending & Acceleration is the rate of change in velocity to the change in time.

How to calculate Drag in Accelerated Flight?

The Drag in Accelerated Flight refers to the aerodynamic force that opposes the motion of an aircraft as it moves through the air, it acts in the direction opposite to the aircraft's velocity vector, this equation appears to calculate the total drag force during climb flight by considering the thrust from the engines, the weight component opposing the flight path, and any additional acceleration experienced by the aircraft is calculated using Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration. To calculate Drag in Accelerated Flight, you need Thrust (T), Thrust Angle (σ_T), Mass of Aircraft (m), Flight Path Angle (γ) & Acceleration (a). With our tool, you need to enter the respective value for Thrust, Thrust Angle, Mass of Aircraft, Flight Path Angle & Acceleration 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 Drag Force?

In this formula, Drag Force uses Thrust, Thrust Angle, Mass of Aircraft, Flight Path Angle & Acceleration. We can use 1 other way(s) to calculate the same, which is/are as follows -

Drag Force = Thrust-(Excess Power/Velocity)

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