Thrust-to-Weight Ratio given Minimum Coefficient of Drag Calculator

✖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 ratio of an aircraft's weight to the total wing area.ⓘ 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 [q]			+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 Minimum Coefficient of Drag [TW]

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Thrust-to-Weight Ratio given 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
TW = (C_Dmin/W_S+k*(n/q)^2*W_S)*q
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 ratio of an aircraft's weight to the total wing area.
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: 1.3 --> No Conversion Required
Wing Loading: 5 Pascal --> 5 Pascal No Conversion Required
Lift Induced Drag Constant: 0.04 --> No Conversion Required
Load Factor: 1.1 --> No Conversion Required
Dynamic Pressure: 2 Pascal --> 2 Pascal No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

TW = (C_Dmin/W_S+k*(n/q)^2*W_S)*q --> (1.3/5+0.04*(1.1/2)^2*5)*2

Evaluating ... ...

TW = 0.641

STEP 3: Convert Result to Output's Unit

0.641 --> No Conversion Required

FINAL ANSWER

0.641 <-- Thrust-to-Weight Ratio

(Calculation completed in 00.004 seconds)

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Thrust-to-Weight Ratio given Minimum Coefficient of Drag Formula

LaTeX Go

Thrust-to-Weight Ratio = (Minimum Drag Coefficient/Wing Loading+Lift Induced Drag Constant*(Load Factor/Dynamic Pressure)^2*Wing Loading)*Dynamic Pressure
TW = (C_Dmin/W_S+k*(n/q)^2*W_S)*q

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 Minimum Coefficient of Drag?

Thrust-to-Weight Ratio given 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 Minimum Coefficient of Drag provides insight into the aircraft's climbing ability and acceleration potential, offering a comprehensive assessment of its performance characteristics. Thrust-to-Weight Ratio is denoted by TW symbol.

How to calculate Thrust-to-Weight Ratio given Minimum Coefficient of Drag using this online calculator? To use this online calculator for Thrust-to-Weight Ratio given Minimum Coefficient of Drag, enter Minimum Drag Coefficient (C_Dmin), Wing Loading (W_S), Lift Induced Drag Constant (k), Load Factor (n) & Dynamic Pressure (q) and hit the calculate button. Here is how the Thrust-to-Weight Ratio given Minimum Coefficient of Drag calculation can be explained with given input values -> 0.641 = (1.3/5+0.04*(1.1/2)^2*5)*2.

FAQ

What is Thrust-to-Weight Ratio given Minimum Coefficient of Drag?

The Thrust-to-Weight Ratio given Minimum Coefficient of Drag provides insight into the aircraft's climbing ability and acceleration potential, offering a comprehensive assessment of its performance characteristics and is represented as TW = (C_Dmin/W_S+k*(n/q)^2*W_S)*q 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 ratio of an aircraft's weight to the total wing area, 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 Minimum Coefficient of Drag?

The Thrust-to-Weight Ratio given Minimum Coefficient of Drag provides insight into the aircraft's climbing ability and acceleration potential, offering a comprehensive assessment of its performance characteristics 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 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 (q). 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.

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