Question

The total wing area of a Boeing B-29 is 1736 ft. The fully loaded take-off mass of a B-29 is 6.25 x 104 kg. The cruising speed of the B-29 is 275 mi/h. At cruising altitude, the air temperature is 251 K and the air pressure is 6.16 x 10Pa. a. Use the density form of the ideal gas law (assuming the average molar mass of the air is 0.0288 kg moll) to compute the air density at cruising altitude in kg/m² b. Calculate the pressure difference AP between the upper and lower wing surfaces required to generate the appropriate lift for the given aircraft mass and wing area (in Pa). c. Assuming the air speed across the lower wing surface is the aircraft speed in the air, use Bernoulli's Equation to calculate the effective air speed over the upper wing surface (in m/s and mi/h) necessary to generate the lift needed to keep the fully loaded aircraft in level flight.

Answer 1

eal We Know that PV-nRT m naM of m-molu ras m RT P - pRT Le P Pneswe Tempenatwre of fe Jcs T densit of +k nivensd Jos Cantant 8 314 So P m pT 4 6.16 0 N/m L 0.028 g. mol T 251 K

6.10 . 0 288 8.314 m3 0. 8 S o3 8 OS 73 ЭР- O.S 0.304 0f tLe A = 1736 36Co. 30 4) A Plane weiht of Tne W mg fenence Zhe then, АP- A A 6.25x 104 9.8 N/m (o. 3049) 36 3797 7506 5 N/m St tltE N/ afpnin

air Speed above Le Рреwwe wm Se eed air & be low the uimg pespectivel., melatig te insignifitant Pneswe chande n to idth of The wing 2 +Le - P) дР 2ΔΡ nen 275 m/hn 60 34 » 13 25 360D

2r 392. Is O65 o. 95o13 0o 5a3 235 1.6034 > V. 3 6 UD S S. 0 294 32 m/s CaPp pon 15 S. 07 mIs