Dynamic pressure at vertical tail for given vertical tail efficiency Solution

STEP 0: Pre-Calculation Summary
Formula Used
Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure
Qv = ηv*Qw
This formula uses 3 Variables
Variables Used
Vertical tail dynamic pressure - (Measured in Pascal) - Vertical tail dynamic pressure is the dynamic pressure associated with the vertical tail of an aircraft.
Vertical tail efficiency - Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft.
Wing dynamic pressure - (Measured in Pascal) - Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
STEP 1: Convert Input(s) to Base Unit
Vertical tail efficiency: 0.6 --> No Conversion Required
Wing dynamic pressure: 0.66 Pascal --> 0.66 Pascal No Conversion Required
STEP 2: Evaluate Formula
Substituting Input Values in Formula
Qv = ηv*Qw --> 0.6*0.66
Evaluating ... ...
Qv = 0.396
STEP 3: Convert Result to Output's Unit
0.396 Pascal --> No Conversion Required
FINAL ANSWER
0.396 Pascal <-- Vertical tail dynamic pressure
(Calculation completed in 00.020 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 Sanjay Krishna
Amrita School of Engineering (ASE), Vallikavu
Sanjay Krishna has verified this Calculator and 200+ more calculators!

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

Dynamic pressure at vertical tail for given vertical tail efficiency Formula

Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure
Qv = ηv*Qw

What is a tailless aircraft?

A tailless aircraft has no tail assembly and no other horizontal surface besides its main wing. The aerodynamic control and stabilization functions in both pitch and roll are incorporated into the main wing.

How to Calculate Dynamic pressure at vertical tail for given vertical tail efficiency?

Dynamic pressure at vertical tail for given vertical tail efficiency calculator uses Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure to calculate the Vertical tail dynamic pressure, The Dynamic pressure at vertical tail for given vertical tail efficiency is a function of the dynamic pressure at wing. Vertical tail dynamic pressure is denoted by Qv symbol.

How to calculate Dynamic pressure at vertical tail for given vertical tail efficiency using this online calculator? To use this online calculator for Dynamic pressure at vertical tail for given vertical tail efficiency, enter Vertical tail efficiency v) & Wing dynamic pressure (Qw) and hit the calculate button. Here is how the Dynamic pressure at vertical tail for given vertical tail efficiency calculation can be explained with given input values -> 0.396 = 0.6*0.66.

FAQ

What is Dynamic pressure at vertical tail for given vertical tail efficiency?
The Dynamic pressure at vertical tail for given vertical tail efficiency is a function of the dynamic pressure at wing and is represented as Qv = ηv*Qw or Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure. Vertical tail efficiency is the tail efficiency associated with the vertical tail of an aircraft & Wing dynamic pressure is the dynamic pressure associated with the wing of an aircraft.
How to calculate Dynamic pressure at vertical tail for given vertical tail efficiency?
The Dynamic pressure at vertical tail for given vertical tail efficiency is a function of the dynamic pressure at wing is calculated using Vertical tail dynamic pressure = Vertical tail efficiency*Wing dynamic pressure. To calculate Dynamic pressure at vertical tail for given vertical tail efficiency, you need Vertical tail efficiency v) & Wing dynamic pressure (Qw). With our tool, you need to enter the respective value for Vertical tail efficiency & Wing dynamic pressure 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 Vertical tail dynamic pressure?
In this formula, Vertical tail dynamic pressure uses Vertical tail efficiency & Wing dynamic pressure. We can use 2 other way(s) to calculate the same, which is/are as follows -
  • 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)
  • 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))
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