Incompressible & Compressible Aerodynamics

Consider two rockets P and Q fired vertically up wi th identical specific impulse and a payload of 2 kg. Rocket P has 2 identical stages, and each stage has 200 kg of propellant and 20 kg of structural weight. Rocket Q has a single stage with 400 kg of propellant and 40 kg of structural weight. Neglecting drag and gravity effects, the ratio of the change in velocity of P to that attained by Q is (A) 1.13 (B) 1.23 (C ) 1.33 (D) 1.43 Common Data Questions Common Data for Questions 48 and 49: Data for an airplane are given as follows: weight 30Wk N , thrust available at sea-level 0 4000TN , wing planform area 230Sm , maximum lift coefficient max 1.4LC  , and drag coefficient 20.015 0.024 .D LCC Assume air density at sea-level 31.22 /kg m  .