## Thrust-to-Weight ratio given vertical velocity Solution

STEP 0: Pre-Calculation Summary
Formula Used
T/W = ((Vv/Va)+ ((Pdynamic/WS)* (CDmin))+ ((k /Pdynamic)* (WS)))
This formula uses 7 Variables
Variables Used
Thrust-to-weight ratio - Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.
Vertical Airspeed - (Measured in Meter per Second) - Vertical Airspeed is the rate at which the airplane ascends or descends.
Aircraft Velocity - (Measured in Meter per Second) - Aircraft Velocity is the maximum speed in the takeoff at which the pilot must take the first action.
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.
Minimum Drag Coefficient - Minimum Drag Coefficient is the product of flat plate skin friction coefficient(Cf) and the ratio of wetted surface area to reference area(swet/sref).
Lift Induced Drag Constant - Lift Induced Drag Constant is the reciprocal of the product of the Aspect ratio, Oswald efficiency factor and pi.
STEP 1: Convert Input(s) to Base Unit
Vertical Airspeed: 100 Knot --> 51.4444444444446 Meter per Second (Check conversion here)
Aircraft Velocity: 400 Knot --> 205.777777777778 Meter per Second (Check conversion here)
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
Wing Loading: 5 Newton per Square Meter --> 5 Pascal (Check conversion here)
Minimum Drag Coefficient: 10 --> No Conversion Required
Lift Induced Drag Constant: 25 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T/W = ((Vv/Va)+ ((Pdynamic/WS)* (CDmin))+ ((k /Pdynamic)* (WS))) --> ((51.4444444444446/205.777777777778)+ ((10/5)* (10))+ ((25 /10)* (5)))
Evaluating ... ...
T/W = 32.75
STEP 3: Convert Result to Output's Unit
32.75 --> No Conversion Required
32.75 <-- Thrust-to-weight ratio
(Calculation completed in 00.031 seconds)
You are here -
Home »

## Credits

Created by Kartikay Pandit
National Institute Of Technology (NIT), Hamirpur
Kartikay Pandit has created this Calculator and 10+ more calculators!
Verified by Anshika Arya
National Institute Of Technology (NIT), Hamirpur
Anshika Arya has verified this Calculator and 2600+ more calculators!

## < 10+ Aircraft Conceptual Design Calculators

Summations of priorities of objectives that need to be maximized (Millitary planes)
Priority Sum of objectives to be maximized (%) = Performance Priority (%)+Flight Quality Priority (%)+Scariness Priority (%)+Maintainability Priority (%)+Producibility Priority (%)+Disposability Priority (%)+Stealth Priority (%) Go
Weight Priority (%) = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Index Go
Cost Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Index Go
Period Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Index Go
Period Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Priority (%) Go
Weight Index = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Priority (%) Go
Cost Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Priority (%) Go
Minimum Design Index = ((Cost Index*Cost Priority (%))+(Weight Index*Weight Priority (%))+(Period Index*Period Priority (%)))/100 Go
Summation of priorities of all objectives that need to be minimized
Priority Sum of objectives to be minimized(%) = Cost Priority (%)+Weight Priority (%)+Period Priority (%) Go
Propulsion Net Thrust
Thrust force = Air Mass Flow Rate*(Velocity of Jet-Flight velocity) Go

## Thrust-to-Weight ratio given vertical velocity Formula

T/W = ((Vv/Va)+ ((Pdynamic/WS)* (CDmin))+ ((k /Pdynamic)* (WS)))

## What is load factor and banking angle?

Load factor is the inverse of the cosine of the banking angle of the aircraft. The bank angle required to conduct a turn at a specific rate is directly proportional to True Airspeed (TAS).

## How to Calculate Thrust-to-Weight ratio given vertical velocity?

Thrust-to-Weight ratio given vertical velocity calculator uses Thrust-to-weight ratio = ((Vertical Airspeed/Aircraft Velocity)+ ((Dynamic Pressure/Wing Loading)* (Minimum Drag Coefficient))+ ((Lift Induced Drag Constant /Dynamic Pressure)* (Wing Loading))) to calculate the Thrust-to-weight ratio, The Thrust-to-Weight ratio given vertical velocity formula is used to determine the required desired rate of climb in terms of the vertical velocity and the minimum coefficient of drag. Thrust-to-weight ratio is denoted by T/W symbol.

How to calculate Thrust-to-Weight ratio given vertical velocity using this online calculator? To use this online calculator for Thrust-to-Weight ratio given vertical velocity, enter Vertical Airspeed (Vv), Aircraft Velocity (Va), Dynamic Pressure (Pdynamic), Wing Loading (WS), Minimum Drag Coefficient (CDmin) & Lift Induced Drag Constant (k) and hit the calculate button. Here is how the Thrust-to-Weight ratio given vertical velocity calculation can be explained with given input values -> 32.75 = ((51.4444444444446/205.777777777778)+ ((10/5)* (10))+ ((25 /10)* (5))) .

### FAQ

What is Thrust-to-Weight ratio given vertical velocity?
The Thrust-to-Weight ratio given vertical velocity formula is used to determine the required desired rate of climb in terms of the vertical velocity and the minimum coefficient of drag and is represented as T/W = ((Vv/Va)+ ((Pdynamic/WS)* (CDmin))+ ((k /Pdynamic)* (WS))) or Thrust-to-weight ratio = ((Vertical Airspeed/Aircraft Velocity)+ ((Dynamic Pressure/Wing Loading)* (Minimum Drag Coefficient))+ ((Lift Induced Drag Constant /Dynamic Pressure)* (Wing Loading))) . Vertical Airspeed is the rate at which the airplane ascends or descends, Aircraft Velocity is the maximum speed in the takeoff at which the pilot must take the first action, Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid, Wing Loading is the loaded weight of the aircraft divided by the area of the wing, Minimum Drag Coefficient is the product of flat plate skin friction coefficient(Cf) and the ratio of wetted surface area to reference area(swet/sref) & Lift Induced Drag Constant is the reciprocal of the product of the Aspect ratio, Oswald efficiency factor and pi.
How to calculate Thrust-to-Weight ratio given vertical velocity?
The Thrust-to-Weight ratio given vertical velocity formula is used to determine the required desired rate of climb in terms of the vertical velocity and the minimum coefficient of drag is calculated using Thrust-to-weight ratio = ((Vertical Airspeed/Aircraft Velocity)+ ((Dynamic Pressure/Wing Loading)* (Minimum Drag Coefficient))+ ((Lift Induced Drag Constant /Dynamic Pressure)* (Wing Loading))) . To calculate Thrust-to-Weight ratio given vertical velocity, you need Vertical Airspeed (Vv), Aircraft Velocity (Va), Dynamic Pressure (Pdynamic), Wing Loading (WS), Minimum Drag Coefficient (CDmin) & Lift Induced Drag Constant (k). With our tool, you need to enter the respective value for Vertical Airspeed, Aircraft Velocity, Dynamic Pressure, Wing Loading, Minimum Drag Coefficient & Lift Induced Drag Constant 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-to-weight ratio?
In this formula, Thrust-to-weight ratio uses Vertical Airspeed, Aircraft Velocity, Dynamic Pressure, Wing Loading, Minimum Drag Coefficient & Lift Induced Drag Constant. We can use 1 other way(s) to calculate the same, which is/are as follows -