1. Consider an airfoil at 12^o angle of attack. The normal and axial force coefficients are 1.2 and 0.03, respectively. Calculate the lift and dragcoefficients.

2. A U-tube mercury manometer is used to measure the pressure at a point on the wing of a wind-tunnel model. One side of the manometer is connected to the model, and the other side is open to the atmosphere. Atmospheric pressure and the density of liquid mercury are 1.01×10⁵ N/m² and 1.36×10⁴ kg/m³, respectively. When the displacement of the two columns of mercury is 20 cm, with the high column on the model side, what is the pressure on the wing?

3. Consider an airfoil at 8 deg. angle of attack. The normal and axial force coefficients are 1.5 and 0.04, respectively. Calculate the lift (CL) and drag (CD) coefficients.

For most gases at standard or near standard conditions, the relationship among pressure, density, and temperature is given by the perfect gas equation of state: p =ρRT, where R is the specific gas constant. For air at near standard conditions, R = 287 J / (kg * K) in the International System of Units and R = 1716 ft * lb / (slug * °R) in the English Engineering System of Units. Using this information, consider the following two cases:

4. At a given point on the wing of the Boeing 727, the pressure and temperature of the air are 1.3 x 10^4N/m2 and 198 K, respectively. Calculate the density at this point.

5. At a point in the test section of the supersonic wind tunnel, the pressure and density of the air are 1118 lb/ft2 and 1.76 x 10^-3 slug/ft3, respectively. Calculate the temperature at this point.