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

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✖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).ⓘ Minimum Drag Coefficient [C_Dmin]			+10% -10%
✖Wing Loading is the loaded weight of the aircraft divided by the area of the wing.ⓘ Wing Loading [W_S]			+10% -10%
✖Lift Induced Drag Constant is the reciprocal of the product of the Aspect ratio, Oswald efficiency factor and pi.ⓘ Lift Induced Drag Constant [k]			+10% -10%
✖Load factor is the ratio of the aerodynamic force on the aircraft to the gross weight of the aircraft.ⓘ Load factor [n]			+10% -10%
✖Dynamic Pressure is simply a convenient name for the quantity which represents the decrease in the pressure due to the velocity of the fluid.ⓘ Dynamic Pressure [P_dynamic]			+10% -10%

✖Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine.ⓘ Thrust-to-Weight ratio given the minimum coefficient of drag [T/W]

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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 = ((C_Dmin/W_S)+((k)*((n/P_dynamic)^(2))*(W_S)))*(P_dynamic)
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 = ((C_Dmin/W_S)+((k)*((n/P_dynamic)^(2))*(W_S)))*(P_dynamic) --> ((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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Sri sivasubramaniyanadar college of engineering (ssn college of engineering), Chennai

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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

Priority of objective weight in design process given minimum design index

Weight Priority (%) = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Index Go

Priority of objective cost in design process given minimum design index

Cost Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Index Go

Priority of objective period of design given minimum design index

Period Priority (%) = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Index Go

Period of design index in terms of minimum design index

Period Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Cost Index*Cost Priority (%)))/Period Priority (%) Go

Weight index in terms of minimum design index

Weight Index = ((Minimum Design Index*100)-(Cost Index*Cost Priority (%))-(Period Index*Period Priority (%)))/Weight Priority (%) Go

Cost index in terms of minimum design index

Cost Index = ((Minimum Design Index*100)-(Weight Index*Weight Priority (%))-(Period Index*Period Priority (%)))/Cost Priority (%) Go

Minimum design index

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 the minimum coefficient of drag Formula

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 (C_Dmin), Wing Loading (W_S), Lift Induced Drag Constant (k), Load factor (n) & Dynamic Pressure (P_dynamic) 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 = ((C_Dmin/W_S)+((k)*((n/P_dynamic)^(2))*(W_S)))*(P_dynamic) 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 (C_Dmin), Wing Loading (W_S), Lift Induced Drag Constant (k), Load factor (n) & Dynamic Pressure (P_dynamic). 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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