Wingspan for given vertical tail volume ratio Solution

STEP 0: Pre-Calculation Summary
Formula Used
Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio)
b = 𝒍v*Sv/(S*Vv)
This formula uses 5 Variables
Variables Used
Wingspan - (Measured in Meter) - The Wingspan (or just span) of a bird or an airplane is the distance from one wingtip to the other wingtip.
Vertical tail moment arm - (Measured in Meter) - The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft.
Vertical tail area - (Measured in Square Meter) - The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline.
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.
Vertical Tail Volume Ratio - Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan.
STEP 1: Convert Input(s) to Base Unit
Vertical tail moment arm: 1.2 Meter --> 1.2 Meter No Conversion Required
Vertical tail area: 5 Square Meter --> 5 Square Meter No Conversion Required
Reference Area: 5.08 Square Meter --> 5.08 Square Meter No Conversion Required
Vertical Tail Volume Ratio: 1.5 --> No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
b = 𝒍v*Sv/(S*Vv) --> 1.2*5/(5.08*1.5)
Evaluating ... ...
b = 0.78740157480315
STEP 3: Convert Result to Output's Unit
0.78740157480315 Meter --> No Conversion Required
FINAL ANSWER
0.78740157480315 0.787402 Meter <-- Wingspan
(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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13 Wing-Tail Interaction Calculators

Sideslip angle for given yawing moment coefficient
Go Sideslip angle = (Yawing moment coefficient/(Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope/(Reference Area*Wingspan*Wing dynamic pressure)))-Sidewash angle
Wingspan for yawing moment coefficient given sideslip angle and sidewash angle
Go Wingspan = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Yawing moment coefficient*Wing dynamic pressure)
Dynamic pressure at vertical tail for given yawing moment coefficient
Go Vertical tail dynamic pressure = Yawing moment coefficient*Reference Area*Wingspan*Wing dynamic pressure/(Vertical tail moment arm*Vertical tail area*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle))
Dynamic pressure at wing for given yawing moment coefficient
Go Wing dynamic pressure = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Wingspan*Yawing moment coefficient)
Wing area for given yawing moment coefficient
Go Reference Area = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Yawing moment coefficient*Wingspan*Wing dynamic pressure)
Vertical tail dynamic pressure for given moment
Go Vertical tail dynamic pressure = Moment produced by vertical tail/(Vertical tail moment arm*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)*Vertical tail area)
Wing dynamic pressure for given yawing moment coefficient
Go Wing dynamic pressure = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wingspan)
Wing area for given moment produced by vertical tail
Go Reference Area = Moment produced by vertical tail/(Yawing moment coefficient*Wing dynamic pressure*Wingspan)
Wingspan for given yawing moment coefficient
Go Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure)
Wing area for given vertical tail volume ratio
Go Reference Area = Vertical tail moment arm*Vertical tail area/(Wingspan*Vertical Tail Volume Ratio)
Wingspan for given vertical tail volume ratio
Go Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio)
Dynamic pressure at vertical tail for given vertical tail efficiency
Go Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure
Dynamic pressure at wing for given vertical tail efficiency
Go Wing dynamic pressure = Vertical tail dynamic pressure/Vertical tail efficiency

Wingspan for given vertical tail volume ratio Formula

Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio)
b = 𝒍v*Sv/(S*Vv)

What is the disadvantage of a T-tail?

A T-tail aircraft may be prone to suffering a dangerous deep stall condition, where a stalled wing at high angles of attack may blank the airflow over the tailplane and elevators, thereby leading to loss of pitch control.

How to Calculate Wingspan for given vertical tail volume ratio?

Wingspan for given vertical tail volume ratio calculator uses Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio) to calculate the Wingspan, The Wingspan for given vertical tail volume ratio depends on the vertical tail moment arm, vertical tail area, and reference wing area. Wingspan is denoted by b symbol.

How to calculate Wingspan for given vertical tail volume ratio using this online calculator? To use this online calculator for Wingspan for given vertical tail volume ratio, enter Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Reference Area (S) & Vertical Tail Volume Ratio (Vv) and hit the calculate button. Here is how the Wingspan for given vertical tail volume ratio calculation can be explained with given input values -> 0.787402 = 1.2*5/(5.08*1.5).

FAQ

What is Wingspan for given vertical tail volume ratio?
The Wingspan for given vertical tail volume ratio depends on the vertical tail moment arm, vertical tail area, and reference wing area and is represented as b = 𝒍v*Sv/(S*Vv) or Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio). The vertical tail moment arm is the distance between the centroid of the vertical tail shape and the center of gravity of the aircraft, The vertical tail area is the area of the surface of the vertical tail, including the submerged area to the fuselage centerline, 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 & Vertical Tail Volume Ratio relates the area of the vertical tail, the distance between the centroid of vertical tail area and aircraft's c.g., the wing area, and the wingspan.
How to calculate Wingspan for given vertical tail volume ratio?
The Wingspan for given vertical tail volume ratio depends on the vertical tail moment arm, vertical tail area, and reference wing area is calculated using Wingspan = Vertical tail moment arm*Vertical tail area/(Reference Area*Vertical Tail Volume Ratio). To calculate Wingspan for given vertical tail volume ratio, you need Vertical tail moment arm (𝒍v), Vertical tail area (Sv), Reference Area (S) & Vertical Tail Volume Ratio (Vv). With our tool, you need to enter the respective value for Vertical tail moment arm, Vertical tail area, Reference Area & Vertical Tail Volume Ratio 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 Wingspan?
In this formula, Wingspan uses Vertical tail moment arm, Vertical tail area, Reference Area & Vertical Tail Volume Ratio. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • Wingspan = Moment produced by vertical tail/(Yawing moment coefficient*Reference Area*Wing dynamic pressure)
  • Wingspan = Vertical tail moment arm*Vertical tail area*Vertical tail dynamic pressure*Vertical tail Lift curve slope*(Sideslip angle+Sidewash angle)/(Reference Area*Yawing moment coefficient*Wing dynamic pressure)
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