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
FD = T*cos(σT)-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
FD = T*cos(σT)-m*[g]*sin(γ)-m*a --> 700*cos(0.034)-20*[g]*sin(0.062)-20*30.37
Evaluating ... ...
FD = 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 00.020 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!

16 Climbing Flight Calculators

Velocity in Accelerated Flight
Go Velocity = (Radius of Curvature/Mass of Aircraft*(Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)))^(1/2)
Lift in Accelerated Flight
Go Lift Force = Mass of Aircraft*[g]*cos(Flight Path Angle)+Mass of Aircraft*Velocity^2/Radius of Curvature-Thrust*sin(Thrust Angle)
Thrust in Accelerated Flight
Go Thrust = (sec(Thrust Angle))*(Drag Force+(Mass of Aircraft*[g]*sin(Flight Path Angle))+(Mass of Aircraft*Acceleration))
Drag in Accelerated Flight
Go Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration
Centrifugal Force in Accelerated Flight
Go Centrifugal Force = Lift Force+Thrust*sin(Thrust Angle)-Mass of Aircraft*[g]*cos(Flight Path Angle)
Rate of Climb of Aircraft
Go Rate of Climb = (Power Available-Power Required)/Aircraft weight
Flight path angle at given rate of climb
Go Flight Path Angle = asin(Rate of Climb/Velocity)
Velocity of aircraft at given rate of climb
Go Velocity = Rate of Climb/sin(Flight Path Angle)
Rate of Climb
Go Rate of Climb = Velocity*sin(Flight Path Angle)
Velocity of aircraft for given excess power
Go Velocity = Excess Power/(Thrust-Drag Force)
Thrust available for given excess power
Go Thrust = Drag Force+(Excess Power/Velocity)
Total Drag for given excess power
Go Drag Force = Thrust-(Excess Power/Velocity)
Excess power
Go Excess Power = Velocity*(Thrust-Drag Force)
Weight of aircraft for given excess power
Go Aircraft weight = Excess Power/Rate of Climb
Excess power for given rate of climb
Go Excess Power = Rate of Climb*Aircraft weight
Rate of Climb for given excess power
Go Rate of Climb = Excess Power/Aircraft weight

Drag in Accelerated Flight Formula

Drag Force = Thrust*cos(Thrust Angle)-Mass of Aircraft*[g]*sin(Flight Path Angle)-Mass of Aircraft*Acceleration
FD = T*cos(σT)-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 is a function of thrust, weight, thrust angle, flight path angle, and acceleration of aircraft. Drag Force is denoted by FD 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 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 is a function of thrust, weight, thrust angle, flight path angle, and acceleration of aircraft and is represented as FD = T*cos(σT)-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 is a function of thrust, weight, thrust angle, flight path angle, and acceleration of 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 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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