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Velocity for Maximizing Range given Range for Jet Aircraft Calculator

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Preliminary Design Conceptual Design

✖Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.ⓘ Range of Aircraft [R]			+10% -10%
✖Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.ⓘ Power Specific Fuel Consumption [c]			+10% -10%
✖Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.ⓘ Maximum Lift-to-Drag Ratio of Aircraft [LDmax_ratio]			+10% -10%
✖Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.ⓘ Weight of Aircraft at Beginning of Cruise Phase [W_i]			+10% -10%
✖Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.ⓘ Weight of Aircraft at End of Cruise Phase [W_f]			+10% -10%

✖Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.ⓘ Velocity for Maximizing Range given Range for Jet Aircraft [V_L/D(max)]

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Velocity for Maximizing Range given Range for Jet Aircraft Solution

STEP 0: Pre-Calculation Summary

Formula Used

Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase))
V_L/D(max) = (R*c)/(LDmax_ratio*ln(W_i/W_f))
This formula uses 1 Functions, 6 Variables

Functions Used

ln - The natural logarithm, also known as the logarithm to the base e, is the inverse function of the natural exponential function., ln(Number)

Variables Used

Velocity at Maximum Lift to Drag Ratio - (Measured in Meter per Second) - Velocity at Maximum Lift to Drag Ratio is the velocity when the ratio of lift and drag coefficient is maximum in value. Basically considered for the cruise phase.
Range of Aircraft - (Measured in Meter) - Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel.
Power Specific Fuel Consumption - (Measured in Kilogram per Second per Watt) - Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time.
Maximum Lift-to-Drag Ratio of Aircraft - Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight.
Weight of Aircraft at Beginning of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission.
Weight of Aircraft at End of Cruise Phase - (Measured in Kilogram) - Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

STEP 1: Convert Input(s) to Base Unit

Range of Aircraft: 1000 Kilometer --> 1000000 Meter (Check conversion here)
Power Specific Fuel Consumption: 0.6 Kilogram per Hour per Watt --> 0.000166666666666667 Kilogram per Second per Watt (Check conversion here)
Maximum Lift-to-Drag Ratio of Aircraft: 19.7 --> No Conversion Required
Weight of Aircraft at Beginning of Cruise Phase: 514 Kilogram --> 514 Kilogram No Conversion Required
Weight of Aircraft at End of Cruise Phase: 350 Kilogram --> 350 Kilogram No Conversion Required

STEP 2: Evaluate Formula

Substituting Input Values in Formula

V_L/D(max) = (R*c)/(LDmax_ratio*ln(W_i/W_f)) --> (1000000*0.000166666666666667)/(19.7*ln(514/350))

Evaluating ... ...

V_L/D(max) = 22.0152344416059

STEP 3: Convert Result to Output's Unit

22.0152344416059 Meter per Second -->42.7941922191042 Knot (Check conversion here)

FINAL ANSWER

42.7941922191042 ≈ 42.79419 Knot <-- Velocity at Maximum Lift to Drag Ratio

(Calculation completed in 00.004 seconds)

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< Preliminary Design Calculators

Optimum Range for Jet Aircraft in Cruising Phase

LaTeX Go Range of Aircraft = (Velocity at Maximum Lift to Drag Ratio*Maximum Lift-to-Drag Ratio of Aircraft)/Power Specific Fuel Consumption*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)

Preliminary Take Off Weight Built-up for Manned Aircraft

LaTeX Go Desired Takeoff Weight = Payload Carried+Operating Empty Weight+Fuel Weight to be Carried+Crew Weight

Preliminary Take off Weight Built-Up for Manned Aircraft given Fuel and Empty Weight Fraction

LaTeX Go Desired Takeoff Weight = (Payload Carried+Crew Weight)/(1-Fuel Fraction-Empty Weight Fraction)

Fuel Fraction

LaTeX Go Fuel Fraction = Fuel Weight to be Carried/Desired Takeoff Weight

Velocity for Maximizing Range given Range for Jet Aircraft Formula

LaTeX Go

What is the maximal range of aircraft?

The maximal total range is the maximum distance an aircraft can fly between takeoff and landing, as limited by fuel capacity in powered aircraft, or cross-country speed and environmental conditions in unpowered aircraft. The range can be seen as the cross-country ground speed multiplied by the maximum time in the air. The fuel time limit for powered aircraft is fixed by the fuel load and rate of consumption. When all fuel is consumed, the engines stop and the aircraft will lose its propulsion.

What is the velocity of maximizing range?

For finding out the maximum range of aircraft the Lift to Drag ratio of Aircraft has to be maximum. So the velocity of the Aircraft at the maximum Lift to Drag ratio is meant to be the Velocity of Maximizing Range.

How to Calculate Velocity for Maximizing Range given Range for Jet Aircraft?

Velocity for Maximizing Range given Range for Jet Aircraft calculator uses Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)) to calculate the Velocity at Maximum Lift to Drag Ratio, The Velocity for Maximizing Range given Range for Jet Aircraft refers to the initial velocity at which a projectile should be launched to achieve the greatest horizontal distance traveled under the influence of gravity, this formula for calculating the velocity required for maximizing the lift-to-drag ratio of an aircraft, considering various parameters such as range, power specific fuel consumption, aircraft weight, and the maximum lift-to-drag ratio. Velocity at Maximum Lift to Drag Ratio is denoted by V_L/D(max) symbol.

How to calculate Velocity for Maximizing Range given Range for Jet Aircraft using this online calculator? To use this online calculator for Velocity for Maximizing Range given Range for Jet Aircraft, enter Range of Aircraft (R), Power Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio of Aircraft (LDmax_ratio), Weight of Aircraft at Beginning of Cruise Phase (W_i) & Weight of Aircraft at End of Cruise Phase (W_f) and hit the calculate button. Here is how the Velocity for Maximizing Range given Range for Jet Aircraft calculation can be explained with given input values -> 83.60895 = (1000000*0.000166666666666667)/(19.7*ln(514/350)).

FAQ

What is Velocity for Maximizing Range given Range for Jet Aircraft?

The Velocity for Maximizing Range given Range for Jet Aircraft refers to the initial velocity at which a projectile should be launched to achieve the greatest horizontal distance traveled under the influence of gravity, this formula for calculating the velocity required for maximizing the lift-to-drag ratio of an aircraft, considering various parameters such as range, power specific fuel consumption, aircraft weight, and the maximum lift-to-drag ratio and is represented as V_L/D(max) = (R*c)/(LDmax_ratio*ln(W_i/W_f)) or Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)). Range of Aircraft is defined as the total distance (measured with respect to ground) traversed by the aircraft on a tank of fuel, Power Specific Fuel Consumption is a characteristic of the engine and defined as the weight of fuel consumed per unit power per unit time, Maximum Lift-to-Drag Ratio of Aircraft refers to the highest ratio of lift force to drag force. It represents the optimal balance between lift and drag for maximum efficiency in level flight, Weight of Aircraft at Beginning of Cruise Phase is the weight of the plane just before going to cruise phase of the mission & Weight of Aircraft at End of Cruise Phase is the weight before the loitering/descent/action phase of the mission plan.

How to calculate Velocity for Maximizing Range given Range for Jet Aircraft?

The Velocity for Maximizing Range given Range for Jet Aircraft refers to the initial velocity at which a projectile should be launched to achieve the greatest horizontal distance traveled under the influence of gravity, this formula for calculating the velocity required for maximizing the lift-to-drag ratio of an aircraft, considering various parameters such as range, power specific fuel consumption, aircraft weight, and the maximum lift-to-drag ratio is calculated using Velocity at Maximum Lift to Drag Ratio = (Range of Aircraft*Power Specific Fuel Consumption)/(Maximum Lift-to-Drag Ratio of Aircraft*ln(Weight of Aircraft at Beginning of Cruise Phase/Weight of Aircraft at End of Cruise Phase)). To calculate Velocity for Maximizing Range given Range for Jet Aircraft, you need Range of Aircraft (R), Power Specific Fuel Consumption (c), Maximum Lift-to-Drag Ratio of Aircraft (LDmax_ratio), Weight of Aircraft at Beginning of Cruise Phase (W_i) & Weight of Aircraft at End of Cruise Phase (W_f). With our tool, you need to enter the respective value for Range of Aircraft, Power Specific Fuel Consumption, Maximum Lift-to-Drag Ratio of Aircraft, Weight of Aircraft at Beginning of Cruise Phase & Weight of Aircraft at End of Cruise Phase 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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