Thrust-to-Weight ratio given the minimum coefficient of drag Solution

STEP 0: Pre-Calculation Summary
Formula Used
Thrust-to-weight ratio = ((Minimum Drag Coefficient/Wing Loading)+((Lift Induced Drag Constant)*((Load factor/Dynamic Pressure)^(2))*(Wing Loading)))*(Dynamic Pressure)
T/W = ((CDmin/WS)+((k)*((n/Pdynamic)^(2))*(WS)))*(Pdynamic)
This formula uses 6 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.
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).
Wing Loading - (Measured in Pascal) - Wing Loading is the loaded weight of the aircraft divided by the area of the wing.
Lift Induced Drag Constant - Lift Induced Drag Constant is the reciprocal of the product of the Aspect ratio, Oswald efficiency factor and pi.
Load factor - Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.
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.
STEP 1: Convert Input(s) to Base Unit
Minimum Drag Coefficient: 10 --> No Conversion Required
Wing Loading: 5 Newton per Square Meter --> 5 Pascal (Check conversion here)
Lift Induced Drag Constant: 25 --> No Conversion Required
Load factor: 1.2 --> No Conversion Required
Dynamic Pressure: 10 Pascal --> 10 Pascal No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
T/W = ((CDmin/WS)+((k)*((n/Pdynamic)^(2))*(WS)))*(Pdynamic) --> ((10/5)+((25)*((1.2/10)^(2))*(5)))*(10)
Evaluating ... ...
T/W = 38
STEP 3: Convert Result to Output's Unit
38 --> No Conversion Required
FINAL ANSWER
38 <-- Thrust-to-weight ratio
(Calculation completed in 00.015 seconds)

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Created by Prasana Kannan
Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai
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Thrust-to-Weight ratio given the minimum coefficient of drag Formula

Thrust-to-weight ratio = ((Minimum Drag Coefficient/Wing Loading)+((Lift Induced Drag Constant)*((Load factor/Dynamic Pressure)^(2))*(Wing Loading)))*(Dynamic Pressure)
T/W = ((CDmin/WS)+((k)*((n/Pdynamic)^(2))*(WS)))*(Pdynamic)

What is Wing Loading?

In aerodynamics, wing loading is the total mass of an aircraft or flying animal divided by the area of its wing. The stalling speed of an aircraft in a straight, level flight is partly determined by its wing loading.

How to Calculate Thrust-to-Weight ratio given the minimum coefficient of drag?

Thrust-to-Weight ratio given the minimum coefficient of drag calculator uses Thrust-to-weight ratio = ((Minimum Drag Coefficient/Wing Loading)+((Lift Induced Drag Constant)*((Load factor/Dynamic Pressure)^(2))*(Wing Loading)))*(Dynamic Pressure) to calculate the Thrust-to-weight ratio, The Thrust-to-Weight ratio given the minimum coefficient of drag is used to maintain a specific banking load at a specific velocity without losing any altitude. Thrust-to-weight ratio is denoted by T/W symbol.

How to calculate Thrust-to-Weight ratio given the minimum coefficient of drag using this online calculator? To use this online calculator for Thrust-to-Weight ratio given the minimum coefficient of drag, enter Minimum Drag Coefficient (CDmin), Wing Loading (WS), Lift Induced Drag Constant (k), Load factor (n) & Dynamic Pressure (Pdynamic) and hit the calculate button. Here is how the Thrust-to-Weight ratio given the minimum coefficient of drag calculation can be explained with given input values -> 38 = ((10/5)+((25)*((1.2/10)^(2))*(5)))*(10) .

FAQ

What is Thrust-to-Weight ratio given the minimum coefficient of drag?
The Thrust-to-Weight ratio given the minimum coefficient of drag is used to maintain a specific banking load at a specific velocity without losing any altitude and is represented as T/W = ((CDmin/WS)+((k)*((n/Pdynamic)^(2))*(WS)))*(Pdynamic) or Thrust-to-weight ratio = ((Minimum Drag Coefficient/Wing Loading)+((Lift Induced Drag Constant)*((Load factor/Dynamic Pressure)^(2))*(Wing Loading)))*(Dynamic Pressure) . 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), Wing Loading is the loaded weight of the aircraft divided by the area of the wing, Lift Induced Drag Constant is the reciprocal of the product of the Aspect ratio, Oswald efficiency factor and pi, Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft & Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.
How to calculate Thrust-to-Weight ratio given the minimum coefficient of drag?
The Thrust-to-Weight ratio given the minimum coefficient of drag is used to maintain a specific banking load at a specific velocity without losing any altitude is calculated using Thrust-to-weight ratio = ((Minimum Drag Coefficient/Wing Loading)+((Lift Induced Drag Constant)*((Load factor/Dynamic Pressure)^(2))*(Wing Loading)))*(Dynamic Pressure) . To calculate Thrust-to-Weight ratio given the minimum coefficient of drag, you need Minimum Drag Coefficient (CDmin), Wing Loading (WS), Lift Induced Drag Constant (k), Load factor (n) & Dynamic Pressure (Pdynamic). With our tool, you need to enter the respective value for Minimum Drag Coefficient, Wing Loading, Lift Induced Drag Constant, Load factor & Dynamic Pressure 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 Minimum Drag Coefficient, Wing Loading, Lift Induced Drag Constant, Load factor & Dynamic Pressure. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Thrust-to-weight ratio = ((Vertical Airspeed/Aircraft Velocity)+ ((Dynamic Pressure/Wing Loading)* (Minimum Drag Coefficient))+ ((Lift Induced Drag Constant /Dynamic Pressure)* (Wing Loading)))
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