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Problem Statement: A rocket nozzle has an exit/throat area ratio of 3. The combustion gas mixture at 20 bar and 2500 K is expanded through the nozzle to an atmosphere at 1 bar.The molar mass of the gas mixture is 33.5 kg kmol−1 and 𝛾 =1.2. Assuming the flow process to be isentropic, estimate the […]
pressure ration, mass flow rate per unit area Read More »
The induced drag coefficient (CD,i)(C_{D,i})(CD,i) is a dimensionless number that represents the drag due to the generation of lift by a wing or other lifting surface. It is caused by the creation of wingtip vortices and the associated downwash, which increases the effective angle of attack of the wing, reducing its ability to produce lift
To find the induced drag coefficient Read More »
The drag polar of an airplane relates the drag coefficient (CDC_DCD) to the lift coefficient (CLC_LCL). It is expressed as: CD=CD0+kCL2C_D = C_{D0} + kC_L^2CD=CD0+kCL2 Here, CD0C_{D0}CD0 is the parasite drag coefficient, and kkk is the coefficient of induced drag. To estimate the drag polar, we need to calculate CD0C_{D0}CD0 and kkk.
Calculate Parasite Drag Coefficient for horizontal and vertical tail contribution Read More »
