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From what i've read drag coefficient at mach 1 is several times (up to 10x) the drag coefficient below drag divergence mach number. It drops as the mach number increases.

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It's easy to find plots representing experimental data for Cd vs M, but I wonder what's the relationship between drag FORCE and mach number. I wasn't able to find a plot for this. I wonder if an aircraft that can reach Mach 1 can automatically reach say mach 1.2, given that even though Cd drops the drag still increases with the square of speed (and engine power required is cubed)

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The amount of drag is related to the coefficient of drag by the following formula:

$$D = C_d (\frac{\rho V^2}{2}) A$$

Where

  • $D$ is the drag
  • $C_d$ is the coefficient of drag
  • $\rho$ is the density of the air the aircraft is moving through
  • $V$ is the velocity of the aircraft
  • $A$ is the reference area of the aircraft.

That last value may require some explanation. Drag is typically measured directly, such as in a wind tunnel, rather than being calculated. It's the coefficient that's usually calculated, and to do so, you need to pick an area. You can use the frontal area of the aircraft, the total skin area, or certain other areas. Each choice of reference area will yield a different value for the $C_d$, so to get from the coefficient back to the actual drag force, you need to know the reference area that was originally used to go the other way.

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Aerodynamic drag is described in the form of a product of:

  • Moving body shape parameter $C_D$
  • Dynamic pressure q.
  • Reference area.

For incompressible flow, dynamic pressure can be taken as $\frac{1}{2} \rho V^2$, with $\rho$ = air density. For compressible flow, dynamic pressure depends on the local speed of sound : q = $\frac{1}{2} \gamma p M^2$, with p being static air pressure and $\gamma$ = ratio of specific heats = 1.4 for air at sea level.

So the drag equation becomes $$D = C_D. \frac{1}{2} \gamma p M^2. S$$

Engine power cubed is of very little relevance in this situation. High subsonic and transsonic aeroplanes are powered by jet engines, which deliver exhaust thrust.

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