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Assume that, at a point on the wing of the
Concorde supersonic transport, the air
temperature is -0.6°C and the pressure is
1.64 × 10^4 N/m 2. Calculate the density
(in kg/m^3) at this point.
Note: Specific Heat of Air in Metric Unit. R
= 287 J/kg*K

Assume That At A Point On The Wing Of The Concorde Supersonic Transport The Air Temperature Is 06C And The Pressure Is 164 104 Nm 2 Calculate The Density In Kgm class=

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