Finding Airspeed: Pressure Altitude, Temp & Mach Number

  • Thread starter Thread starter physics_197
  • Start date Start date
Click For Summary
SUMMARY

The discussion focuses on calculating equivalent airspeed (Veq), total pressure at the pitot tube, and both correctly and incorrectly calibrated airspeed for a scenario involving a pressure altitude of 12 km, an ambient temperature of 15 degrees Celsius above standard atmosphere, and a cruise Mach number of 0.85. Key equations used include Veq = sqrt(sigma) * V, M = V/a, and T = Tsea + a(h-hs). The user seeks clarification on the use of temperature in determining sigma and the distinction between correct and incorrect airspeed calibrations.

PREREQUISITES
  • Understanding of pressure altitude and its implications in aviation.
  • Familiarity with the concept of Mach number and its calculation.
  • Knowledge of the standard atmosphere and temperature variations.
  • Basic grasp of aerodynamic equations related to airspeed calculations.
NEXT STEPS
  • Study the calculation of sigma in relation to temperature variations at altitude.
  • Learn about the differences between true airspeed and calibrated airspeed.
  • Research the effects of temperature on air density and its impact on flight performance.
  • Explore online resources or textbooks that cover advanced aerodynamics and airspeed calculations.
USEFUL FOR

Aerospace engineering students, pilots, and aviation professionals involved in flight performance analysis and airspeed calculations.

physics_197
Messages
27
Reaction score
0

Homework Statement



Pressure altitude of 12km,
Ambient temp is 15 celsius above that of the standard atmosphere,
cruise mach number is 0.85.

Find equivalent airspeed, total pressure at pitot tube, correctly calibrated airspeed, and incorrectly calibrated airspeed (Compression is ignored).

Homework Equations



Veq = sqr(sigma)*V
M = V/a
T = Tsea + a(h-hs)

The Attempt at a Solution


[/B]
Here is my process, please correct if needed, I took the altitude and found out what the temp should be. Then do I go and find sigma by using this temp I just found or use the 15 degrees above it? Then I should be able to use Mach to find the true airspeed and plug those into the eqn to find Veq.

And then, what is the difference between correct and uncorrect? The notes are very bare in these terms.

Thanks, feel free to ask questions!
 
Physics news on Phys.org
Can you provide a reference to an online treatment of this topic?
 

Similar threads

Finding Increse in Volume Given Temp, Vol Expansion....
  • · Replies 8 ·
Replies
8
Views
5K
Calculating air pressure from altitude, RH and temperature?
  • · Replies 3 ·
Replies
3
Views
5K
Convert EAS to TAS: Equations and Solution for a Boeing 747 at 10,000m Altitude
  • · Replies 1 ·
Replies
1
Views
4K
Change of of the pressure of water inside a container
  • · Replies 7 ·
Replies
7
Views
2K
Mean free path and speed as a function of pressure and temp
  • · Replies 1 ·
Replies
1
Views
2K
How Does the Equation of State for a Solid Change with Temperature and Pressure?
  • · Replies 5 ·
Replies
5
Views
3K
Is Total Pressure Constant at the Same Altitude for Any Moving Flow?
  • · Replies 1 ·
Replies
1
Views
4K
Pressure, temp, volume change of water vapor, and steam table clarity
  • · Replies 5 ·
Replies
5
Views
5K
Atmospheric Density from: Alt, Temp, Pressure & Humidity
  • · Replies 2 ·
Replies
2
Views
4K
Solving Piston & Spring Homework Problem - Work, Temp & Heat Input
  • · Replies 6 ·
Replies
6
Views
2K