Tail moment arm for given horizontal tail volume ratio Solution

STEP 0: Pre-Calculation Summary
Formula Used
Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
๐’t = VH*S*cma/St
This formula uses 5 Variables
Variables Used
Horizontal tail moment arm - (Measured in Meter) - The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft.
Horizontal Tail Volume Ratio - Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord.
Reference Area - (Measured in Square Meter) - The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area.
Mean aerodynamic chord - (Measured in Meter) - The Mean aerodynamic chord is a two-dimensional representation of the whole wing.
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
STEP 1: Convert Input(s) to Base Unit
Horizontal Tail Volume Ratio: 1.42 --> No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Mean aerodynamic chord: 0.2 Meter --> 0.2 Meter No Conversion Required
Horizontal tail area: 1.8 Square Meter --> 1.8 Square Meter No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
๐’t = VH*S*cma/St --> 1.42*5.08*0.2/1.8
Evaluating ... ...
๐’t = 0.801511111111111
STEP 3: Convert Result to Output's Unit
0.801511111111111 Meter --> No Conversion Required
FINAL ANSWER
0.801511111111111 โ‰ˆ 0.801511 Meter <-- Horizontal tail moment arm
(Calculation completed in 00.004 seconds)

Credits

Created by Vinay Mishra
Indian Institute for Aeronautical Engineering and Information Technology (IIAEIT), Pune
Vinay Mishra has created this Calculator and 300+ more calculators!
Verified by Shikha Maurya
Indian Institute of Technology (IIT), Bombay
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19 Tail Contribution Calculators

Tail Pitching moment coefficient for given tail efficiency
Go Tail Pitching Moment Coefficient = -(Tail Efficiency*Horizontal tail area*Horizontal tail moment arm*Tail Lift Coefficient)/(Reference Area*Mean aerodynamic chord)
Tail Efficiency for given pitching moment coefficient
Go Tail Efficiency = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Horizontal tail moment arm*Horizontal tail area*Tail Lift Coefficient)
Tail moment arm for given tail moment coefficient
Go Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
Tail area for given tail moment coefficient
Go Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
Mean aerodynamic chord for given tail pitching moment coefficient
Go Mean aerodynamic chord = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Tail Pitching Moment Coefficient)
Tail Pitching moment coefficient
Go Tail Pitching Moment Coefficient = Pitching Moment due to Tail/(0.5*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)
Tail Pitching moment for given moment coefficient
Go Pitching Moment due to Tail = (Tail Pitching Moment Coefficient*Freestream Density*Flight Velocity^2*Reference Area*Mean aerodynamic chord)/2
Tail Pitching moment for given lift coefficient
Go Pitching Moment due to Tail = -(Horizontal tail moment arm*Tail Lift Coefficient*Freestream Density*Tail Velocity^2*Horizontal tail area)/2
Wing Mean aerodynamic chord for given horizontal tail volume ratio
Go Mean aerodynamic chord = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Horizontal Tail Volume Ratio)
Wing Reference area for given horizontal tail volume ratio
Go Reference Area = Horizontal tail moment arm*Horizontal tail area/(Horizontal Tail Volume Ratio*Mean aerodynamic chord)
Horizontal tail volume ratio
Go Horizontal Tail Volume Ratio = Horizontal tail moment arm*Horizontal tail area/(Reference Area*Mean aerodynamic chord)
Tail moment arm for given horizontal tail volume ratio
Go Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
Horizontal tail area for given tail volume ratio
Go Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
Horizontal tail volume ratio for given pitching moment coefficient
Go Horizontal Tail Volume Ratio = -Tail Pitching Moment Coefficient/(Tail Efficiency*Tail Lift Coefficient)
Tail lift coefficient for given tail volume ratio
Go Tail Lift Coefficient = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Efficiency)
Tail Efficiency for given tail volume ratio
Go Tail Efficiency = -Tail Pitching Moment Coefficient/(Horizontal Tail Volume Ratio*Tail Lift Coefficient)
Tail Pitching moment coefficient for given tail volume ratio
Go Tail Pitching Moment Coefficient = -Horizontal Tail Volume Ratio*Tail Efficiency*Tail Lift Coefficient
Tail lift for given tail pitching moment
Go Lift due to tail = -Pitching Moment due to Tail/Horizontal tail moment arm
Pitching moment due to tail
Go Pitching Moment due to Tail = -Horizontal tail moment arm*Lift due to tail

Tail moment arm for given horizontal tail volume ratio Formula

Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area
๐’t = VH*S*cma/St

Can a plane recover from a stall?

To recover from a stall, the pilot must push the nose down. Then the pilot must increase the engine power using the throttle. When airspeed increases again, the pilot can level the wings and pull up to return the aircraft to normal flight.

How to Calculate Tail moment arm for given horizontal tail volume ratio?

Tail moment arm for given horizontal tail volume ratio calculator uses Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area to calculate the Horizontal tail moment arm, The Tail moment arm for given horizontal tail volume ratio is a function of the wing reference area, wing means aerodynamic chord, tail volume ratio, and tail area. Horizontal tail moment arm is denoted by ๐’t symbol.

How to calculate Tail moment arm for given horizontal tail volume ratio using this online calculator? To use this online calculator for Tail moment arm for given horizontal tail volume ratio, enter Horizontal Tail Volume Ratio (VH), Reference Area (S), Mean aerodynamic chord (cma) & Horizontal tail area (St) and hit the calculate button. Here is how the Tail moment arm for given horizontal tail volume ratio calculation can be explained with given input values -> 0.795867 = 1.42*5.08*0.2/1.8.

FAQ

What is Tail moment arm for given horizontal tail volume ratio?
The Tail moment arm for given horizontal tail volume ratio is a function of the wing reference area, wing means aerodynamic chord, tail volume ratio, and tail area and is represented as ๐’t = VH*S*cma/St or Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area. Horizontal Tail Volume Ratio relates the area of the horizontal tail, the distance between tail and aircraft's c.g., the wing area, and the mean aerodynamic wing chord, The Reference Area is arbitrarily an area that is characteristic of the object being considered. For an aircraft wing, the wing's planform area is called the reference wing area or simply wing area, The Mean aerodynamic chord is a two-dimensional representation of the whole wing & The Horizontal tail area is the area of the horizontal tail of an aircraft.
How to calculate Tail moment arm for given horizontal tail volume ratio?
The Tail moment arm for given horizontal tail volume ratio is a function of the wing reference area, wing means aerodynamic chord, tail volume ratio, and tail area is calculated using Horizontal tail moment arm = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail area. To calculate Tail moment arm for given horizontal tail volume ratio, you need Horizontal Tail Volume Ratio (VH), Reference Area (S), Mean aerodynamic chord (cma) & Horizontal tail area (St). With our tool, you need to enter the respective value for Horizontal Tail Volume Ratio, Reference Area, Mean aerodynamic chord & Horizontal tail area and hit the calculate button. You can also select the units (if any) for Input(s) and the Output as well.
How many ways are there to calculate Horizontal tail moment arm?
In this formula, Horizontal tail moment arm uses Horizontal Tail Volume Ratio, Reference Area, Mean aerodynamic chord & Horizontal tail area. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Horizontal tail moment arm = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail area*Tail Lift Coefficient)
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