Design 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%
✖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 [R_H]			+10% -10%

✖Design range RD is the distance achievable when taking off with the maximum take off weight.ⓘ Design range given range increment [R_D]

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Formula

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Design range given range increment

Formula

`"R"_{"D"} = "ΔR"+"R"_{"H"}`

Example

`"3886km"="3000km"+"886km"`

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Design range given range increment Solution

STEP 0: Pre-Calculation Summary

Formula Used

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

Variables Used

Design range - (Measured in Meter) - Design range RD is the distance achievable when taking off with the maximum take off weight.
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.
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.

STEP 1: Convert Input(s) to Base Unit

Range increment of aircraft: 3000 Kilometer --> 3000000 Meter (Check conversion here)
Harmonic range: 886 Kilometer --> 886000 Meter (Check conversion here)

STEP 2: Evaluate Formula

Substituting Input Values in Formula

R_D = ΔR+R_H --> 3000000+886000

Evaluating ... ...

R_D = 3886000

STEP 3: Convert Result to Output's Unit

3886000 Meter -->3886 Kilometer (Check conversion here)

FINAL ANSWER

3886 Kilometer <-- Design 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

Kartikay Pandit has verified this Calculator and 400+ more calculators!

< 25 Preliminary Design Calculators

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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

Design range given range increment Formula

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

What is design range?

The design range is the distance covered by an aircraft with maximum take off weight and design payload.

How to Calculate Design range given range increment?

Design range given range increment calculator uses Design range = Range increment of aircraft+Harmonic range to calculate the Design range, Design range given range increment RD is the distance achievable when taking off with the MTOW and a design payload (DPL) less than the MPL and fuel (point D). The DPL mostly corresponds to a multi-class cabin of a medium or long range airliner. Design range is denoted by R_D symbol.

How to calculate Design range given range increment using this online calculator? To use this online calculator for Design range given range increment, enter Range increment of aircraft (ΔR) & Harmonic range (R_H) and hit the calculate button. Here is how the Design range given range increment calculation can be explained with given input values -> 3.886 = 3000000+886000.

FAQ

What is Design range given range increment?

Design range given range increment RD is the distance achievable when taking off with the MTOW and a design payload (DPL) less than the MPL and fuel (point D). The DPL mostly corresponds to a multi-class cabin of a medium or long range airliner and is represented as R_D = ΔR+R_H or Design range = Range increment of aircraft+Harmonic range. Range increment of aircraft is the maximal total range is the maximum distance an aircraft can fly between takeoff and landing & 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.

How to calculate Design range given range increment?

Design range given range increment RD is the distance achievable when taking off with the MTOW and a design payload (DPL) less than the MPL and fuel (point D). The DPL mostly corresponds to a multi-class cabin of a medium or long range airliner is calculated using Design range = Range increment of aircraft+Harmonic range. To calculate Design range given range increment, you need Range increment of aircraft (ΔR) & Harmonic range (R_H). With our tool, you need to enter the respective value for Range increment of aircraft & Harmonic 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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