Problem 2.34 2.1 MJ/kg, which divides into700 kJ/kg per duct (for three ducts) Problem 2.35 Mcone ≈ 2.4 M 1 ≈ 0.66 or 2.0 ~ 37.2% static pressure drop ~ 145% static pressure rise ~ 6.35% loss of fluid impulse (subsonic) and ~10.93% loss of fluid impulse (supersonic) Problem 2.30 L* ≈ 2.54 m ~ 40.7% total pressure loss Problem 2.24 Therefore, static pressure rise is 466.7% p1 Problem 2.19 P2 ≈ 0.468 and static pressure drop is ~53.23% p1 Problem 2.18
Aircraft propulsion solution manual free#
Region 1 is the free stream condition.Ĭl = 1.732 cd cm, LE = 0.3694 Problem 2.9 M 2 ≈ 3.4 A2 = 3.664 A1 = δ 42.9° Problem 2.7 First, we state that regions 2 and 3 are on the top and region 4 is on the bottom surface of the halfdiamond airfoil. Answers to All Problems in Aircraft Propulsion, 2nd Edition Chapter 1 Problem 1.1 Thermal efficiency is 85.6% Problem 1.2 Thermal efficiency is 66.7% Problem 1.3