Questions: Velocidade aerodinâmica (VA, VV ou TAS): - Calcule a velocidade aerodinâmica nas seguintes condições: - VI = 120kt; Alt = 7000ft; temp = 8°C: 135 kt - VI = 901t'; Alt = 5000ft; temp = 14°C: 98 Kt - VI = 135kt; Alt = 9500ft; temp = 4°C: 158 kt - VI = 120kt; Alt = 8500ft; temp = 0°C:

Solution Steps

The problem involves calculating the true airspeed (TAS) given indicated airspeed (IAS), altitude, and temperature. The TAS can be calculated using the formula that accounts for altitude and temperature effects on air density.

The formula to convert indicated airspeed (IAS) to true airspeed (TAS) is: \[ \text{TAS} = \text{IAS} \times \sqrt{\frac{\rho_0}{\rho}} \] where \(\rho_0\) is the air density at sea level, and \(\rho\) is the air density at the given altitude and temperature. The air density \(\rho\) can be calculated using the International Standard Atmosphere (ISA) model.

For the given conditions, we need to calculate the TAS for the fourth set of conditions: \( \text{VI} = 120 \, \text{kt}, \, \text{Alt} = 8500 \, \text{ft}, \, \text{temp} = 0^\circ \text{C} \).

1. Calculate Air Density at Altitude:

   • Use the ISA model to find the air density at 8500 ft and 0°C.
   • The standard temperature lapse rate is \( -0.0065 \, \text{K/m} \).
   • Convert altitude to meters: \( 8500 \, \text{ft} = 2590.8 \, \text{m} \).
   • Calculate the temperature at altitude: \( T = 288.15 \, \text{K} - 0.0065 \times 2590.8 \).
   • Calculate the pressure at altitude using the barometric formula.
   • Calculate the air density using the ideal gas law.

2. Calculate TAS:

   • Substitute the calculated air density into the TAS formula.
   • Compute the TAS.

Final Answer