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Originally Posted by B767Driver  Are you sure about this? |
Well, D = Cd * (1/2 rho V^2) * A, so you have two variables, rho and V. Now V in that equation is TAS; you can replace it with EAS if you replace rho with rho_0, which is sea level density. Then drag will only vary with EAS.
Doesn't take into account any Mach or Reynold's number effects. Since we're talking about relatively low airspeeds, it doesn't seem that it would be too much of an error.