Tail area for given tail moment coefficient Solution

STEP 0: Pre-Calculation Summary
Formula Used
Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
St = -(Cmt*S*cma)/(ฮท*๐’t*CTlift)
This formula uses 7 Variables
Variables Used
Horizontal tail area - (Measured in Square Meter) - The Horizontal tail area is the area of the horizontal tail of an aircraft.
Tail Pitching Moment Coefficient - Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft.
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.
Tail Efficiency - Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing.
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.
Tail Lift Coefficient - Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
STEP 1: Convert Input(s) to Base Unit
Tail Pitching Moment Coefficient: -0.39 --> 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
Tail Efficiency: 0.92 --> No Conversion Required
Horizontal tail moment arm: 0.8 Meter --> 0.8 Meter No Conversion Required
Tail Lift Coefficient: 0.3 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
St = -(Cmt*S*cma)/(ฮท*๐’t*CTlift) --> -((-0.39)*5.08*0.2)/(0.92*0.8*0.3)
Evaluating ... ...
St = 1.7945652173913
STEP 3: Convert Result to Output's Unit
1.7945652173913 Square Meter --> No Conversion Required
FINAL ANSWER
1.7945652173913 โ‰ˆ 1.794565 Square Meter <-- Horizontal tail area
(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!
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PSG College of Technology (PSGCT), Coimbatore
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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 area for given tail moment coefficient Formula

Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient)
St = -(Cmt*S*cma)/(ฮท*๐’t*CTlift)

What is Super stall?

A Deep Stall, sometimes referred to as a Super Stall, is a hazardous form of a stall that results in a substantial reduction or loss of elevator authority, making normal stall recovery actions ineffective. In many cases, an aircraft in a Deep Stall might be unrecoverable.

How to Calculate Tail area for given tail moment coefficient?

Tail area for given tail moment coefficient calculator uses Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient) to calculate the Horizontal tail area, The Tail area for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail moment arm, and tail lift coefficient. Horizontal tail area is denoted by St symbol.

How to calculate Tail area for given tail moment coefficient using this online calculator? To use this online calculator for Tail area for given tail moment coefficient, enter Tail Pitching Moment Coefficient (Cmt), Reference Area (S), Mean aerodynamic chord (cma), Tail Efficiency (ฮท), Horizontal tail moment arm (๐’t) & Tail Lift Coefficient (CTlift) and hit the calculate button. Here is how the Tail area for given tail moment coefficient calculation can be explained with given input values -> 1.794565 = -((-0.39)*5.08*0.2)/(0.92*0.8*0.3).

FAQ

What is Tail area for given tail moment coefficient?
The Tail area for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail moment arm, and tail lift coefficient and is represented as St = -(Cmt*S*cma)/(ฮท*๐’t*CTlift) or Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient). Tail Pitching Moment Coefficient is the coefficient of pitching moment associated with the horizontal tail of an aircraft, 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, Tail Efficiency is defined as the ratio of dynamic pressure associated with the tail to dynamic pressure associated with an aircraft's wing, The horizontal tail moment arm is the distance between the lift center of the horizontal tail and the center of gravity of the aircraft & Tail Lift Coefficient is the lift coefficient associated with the tail (only) of an aircraft. It is a dimensionless quantity.
How to calculate Tail area for given tail moment coefficient?
The Tail area for given tail moment coefficient is a function of tail pitching moment coefficient, wing reference area, wing mean aerodynamic chord, tail efficiency, tail moment arm, and tail lift coefficient is calculated using Horizontal tail area = -(Tail Pitching Moment Coefficient*Reference Area*Mean aerodynamic chord)/(Tail Efficiency*Horizontal tail moment arm*Tail Lift Coefficient). To calculate Tail area for given tail moment coefficient, you need Tail Pitching Moment Coefficient (Cmt), Reference Area (S), Mean aerodynamic chord (cma), Tail Efficiency (ฮท), Horizontal tail moment arm (๐’t) & Tail Lift Coefficient (CTlift). With our tool, you need to enter the respective value for Tail Pitching Moment Coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail moment arm & Tail Lift Coefficient 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 area?
In this formula, Horizontal tail area uses Tail Pitching Moment Coefficient, Reference Area, Mean aerodynamic chord, Tail Efficiency, Horizontal tail moment arm & Tail Lift Coefficient. We can use 1 other way(s) to calculate the same, which is/are as follows -
  • Horizontal tail area = Horizontal Tail Volume Ratio*Reference Area*Mean aerodynamic chord/Horizontal tail moment arm
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