Harmonic range given range increment Calculator

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✖Range increment of aircraft is the maximal total range is the maximum distance an aircraft can fly between takeoff and landing.ⓘ Range increment of aircraft [ΔR]			+10% -10%
✖Design range RD is the distance achievable when taking off with the maximum take off weight.ⓘ Design range [R_D]			+10% -10%

✖Harmonic range is point that the aircraft is most structurally efficient in terms of payload carriage, and represents the maximum range for the maximum payload.ⓘ Harmonic range given range increment [R_H]

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Formula

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Harmonic range given range increment

Formula

`"R"_{"H"} = "ΔR"+"R"_{"D"}`

Example

`"4220km"="3000km"+"1220km"`

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Harmonic range given range increment Solution

STEP 0: Pre-Calculation Summary

Formula Used

Harmonic range = Range increment of aircraft+Design range
R_H = ΔR+R_D
This formula uses 3 Variables

Variables Used

Harmonic range - (Measured in Meter) - Harmonic range is point that the aircraft is most structurally efficient in terms of payload carriage, and represents the maximum range for the maximum payload.
Range increment of aircraft - (Measured in Meter) - Range increment of aircraft is the maximal total range is the maximum distance an aircraft can fly between takeoff and landing.
Design range - (Measured in Meter) - Design range RD is the distance achievable when taking off with the maximum take off weight.

STEP 1: Convert Input(s) to Base Unit

Range increment of aircraft: 3000 Kilometer --> 3000000 Meter (Check conversion here)
Design range: 1220 Kilometer --> 1220000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R_H = ΔR+R_D --> 3000000+1220000

Evaluating ... ...

R_H = 4220000

STEP 3: Convert Result to Output's Unit

4220000 Meter -->4220 Kilometer (Check conversion here)

FINAL ANSWER

4220 Kilometer <-- Harmonic range

(Calculation completed in 00.004 seconds)

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Credits

Created by Himanshu Sharma

National Institute of Technology, Hamirpur (NITH), Himachal Pradesh

Himanshu Sharma has created this Calculator and 50+ more calculators!

Verified by Kartikay Pandit

National Institute Of Technology (NIT), Hamirpur

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Go Velocity for Maximum Endurance = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Endurance of Aircraft)

Preliminary Endurance for Prop-Driven Aircraft

Go Endurance of Aircraft = (Lift to Drag Ratio at Maximum Endurance*Propeller Efficiency*ln(Weight of Aircraft at Beginning of Loiter Phase/Weight of Aircraft at End of Loiter Phase))/(Power Specific Fuel Consumption*Velocity for Maximum Endurance)

Velocity for Maximizing Range given Range for Jet Aircraft

Go 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))

Optimum Range for Jet Aircraft in Cruising Phase

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)

Optimum Range for Prop-Driven Aircraft in Cruising Phase

Go Range of Aircraft = (Propeller Efficiency*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 Endurance for Jet Aircraft

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

Maximum Lift over Drag

Go Maximum Lift to Drag Ratio of Aircraft = Landing Mass Fraction*((Aspect Ratio of a Wing)/(Aircraft Wetted Area/Reference Area))^(0.5)

Preliminary Take Off Weight Built-up for Manned Aircraft

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

Payload Weight given Takeoff Weight

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

Empty Weight given Takeoff Weight

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

Crew Weight given Takeoff Weight

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

Fuel Weight given Takeoff Weight

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

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

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

Fuel Fraction given Takeoff Weight and Empty Weight Fraction

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

Empty Weight Fraction given Takeoff Weight and Fuel Fraction

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

Payload Weight given Fuel and Empty Weight Fractions

Go Payload Carried = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Crew Weight

Crew Weight given Fuel and Empty Weight Fraction

Go Crew Weight = Desired Takeoff Weight*(1-Empty Weight Fraction-Fuel Fraction)-Payload Carried

Takeoff Weight given Empty Weight Fraction

Go Desired Takeoff Weight = Operating Empty Weight/Empty Weight Fraction

Empty Weight given Empty Weight Fraction

Go Operating Empty Weight = Empty Weight Fraction*Desired Takeoff Weight

Empty Weight Fraction

Go Empty Weight Fraction = Operating Empty Weight/Desired Takeoff Weight

Winglet Friction Coefficient

Go Coefficient of Friction = 4.55/(log10(Winglet Reynolds Number^2.58))

Takeoff Weight given Fuel Fraction

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

Fuel Weight given Fuel Fraction

Go Fuel Weight to be Carried = Fuel Fraction*Desired Takeoff Weight

Fuel Fraction

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

Design range given range increment

Go Design range = Range increment of aircraft+Harmonic range

Harmonic range given range increment Formula

Harmonic range = Range increment of aircraft+Design range
R_H = ΔR+R_D

What is Harmonic range?

This point is sometimes called the “Harmonic Range” of the airplane.. It is at this point that the aircraft is most structurally efficient in terms of payload carriage, and “represents the maximum range for the maximum payload”

How to Calculate Harmonic range given range increment?

Harmonic range given range increment calculator uses Harmonic range = Range increment of aircraft+Design range to calculate the Harmonic range, The Harmonic range given range increment is the general sum of range increment that is given and the design range of the aircraft. Harmonic range is denoted by R_H symbol.

How to calculate Harmonic range given range increment using this online calculator? To use this online calculator for Harmonic range given range increment, enter Range increment of aircraft (ΔR) & Design range (R_D) and hit the calculate button. Here is how the Harmonic range given range increment calculation can be explained with given input values -> 4.22 = 3000000+1220000.

FAQ

What is Harmonic range given range increment?

The Harmonic range given range increment is the general sum of range increment that is given and the design range of the aircraft and is represented as R_H = ΔR+R_D or Harmonic range = Range increment of aircraft+Design range. Range increment of aircraft is the maximal total range is the maximum distance an aircraft can fly between takeoff and landing & Design range RD is the distance achievable when taking off with the maximum take off weight.

How to calculate Harmonic range given range increment?

The Harmonic range given range increment is the general sum of range increment that is given and the design range of the aircraft is calculated using Harmonic range = Range increment of aircraft+Design range. To calculate Harmonic range given range increment, you need Range increment of aircraft (ΔR) & Design range (R_D). With our tool, you need to enter the respective value for Range increment of aircraft & Design range 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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