Thrust-to-Weight Ratio given Vertical Velocity Calculator

✖Vertical Airspeed is the rate at which the airplane ascends or descends.ⓘ Vertical Airspeed [V_v]			+10% -10%
✖Aircraft Velocity is the maximum speed in the takeoff at which the pilot must take the first action.ⓘ Aircraft Velocity [V_a]			+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%
✖Wing Loading is the loaded weight of the aircraft divided by the area of the wing.ⓘ Wing Loading [W_S]			+10% -10%
✖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%
✖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%

✖Thrust-to-Weight Ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, or propeller engine.ⓘ Thrust-to-Weight Ratio given Vertical Velocity [TW]

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Thrust-to-Weight Ratio given Vertical Velocity Solution

STEP 0: Pre-Calculation Summary

Formula Used

Thrust-to-Weight Ratio = ((Vertical Airspeed/Aircraft Velocity)+((Dynamic Pressure/Wing Loading)*(Minimum Drag Coefficient))+((Lift Induced Drag Constant/Dynamic Pressure)*(Wing Loading)))
TW = ((V_v/V_a)+((P_dynamic/W_S)*(C_Dmin))+((k/P_dynamic)*(W_S)))
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, or 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.
Wing Loading - (Measured in Pascal) - Wing Loading is the loaded weight of the aircraft divided by the area of the wing.
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: 54 Meter per Second --> 54 Meter per Second No Conversion Required
Aircraft Velocity: 206 Meter per Second --> 206 Meter per Second No Conversion Required
Dynamic Pressure: 8 Pascal --> 8 Pascal No Conversion Required
Wing Loading: 5 Pascal --> 5 Pascal No Conversion Required
Minimum Drag Coefficient: 1.3 --> No Conversion Required
Lift Induced Drag Constant: 25 --> No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

TW = ((V_v/V_a)+((P_dynamic/W_S)*(C_Dmin))+((k/P_dynamic)*(W_S))) --> ((54/206)+((8/5)*(1.3))+((25/8)*(5)))

Evaluating ... ...

TW = 17.9671359223301

STEP 3: Convert Result to Output's Unit

17.9671359223301 --> No Conversion Required

FINAL ANSWER

17.9671359223301 ≈ 17.96714 <-- Thrust-to-Weight Ratio

(Calculation completed in 00.004 seconds)

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National Institute Of Technology (NIT), Hamirpur

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Thrust-to-Weight Ratio given Vertical Velocity Formula

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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, Thrust-to-Weight Ratio given Vertical Velocity provides a measure of an aircraft's ability to ascend vertically under the influence of its engines, this ratio is particularly important during vertical takeoff, hovering, or vertical landing maneuvers commonly performed by vertical takeoff and landing (VTOL) aircraft or helicopters. Thrust-to-Weight Ratio is denoted by TW 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 (V_v), Aircraft Velocity (V_a), Dynamic Pressure (P_dynamic), Wing Loading (W_S), Minimum Drag Coefficient (C_Dmin) & 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 -> 17.96714 = ((54/206)+((8/5)*(1.3))+((25/8)*(5))).

FAQ

What is Thrust-to-Weight Ratio given Vertical Velocity?

Thrust-to-Weight Ratio given Vertical Velocity provides a measure of an aircraft's ability to ascend vertically under the influence of its engines, this ratio is particularly important during vertical takeoff, hovering, or vertical landing maneuvers commonly performed by vertical takeoff and landing (VTOL) aircraft or helicopters and is represented as TW = ((V_v/V_a)+((P_dynamic/W_S)*(C_Dmin))+((k/P_dynamic)*(W_S))) 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?

Thrust-to-Weight Ratio given Vertical Velocity provides a measure of an aircraft's ability to ascend vertically under the influence of its engines, this ratio is particularly important during vertical takeoff, hovering, or vertical landing maneuvers commonly performed by vertical takeoff and landing (VTOL) aircraft or helicopters 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 (V_v), Aircraft Velocity (V_a), Dynamic Pressure (P_dynamic), Wing Loading (W_S), Minimum Drag Coefficient (C_Dmin) & 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.

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