Problem 3.4 The turning radius r (m) of an aircraft can be calculated with the f

Question

Problem 3.4 The turning radius r (m) of an aircraft can be calculated with the following equation: r=(vm)^/ag2 where v is the aircraft speed (Mach) m is the speed of sound (340 m/s) a is maximum acceleration of the aircraft (2 g) g is the acceleration due to gravity (9.81 m/s^2) Write a function to complete the following tasks: a) Define an input argument for the speed v. The vector v should contain values between 0.5 Mach and 2 Mach. You can choose the number of values in the vector (pick at least 20 values). b) For ALL speed values, calculate the turning radius r given the equation above. c) Output the turning radius r using an output argument. HINT: An output argument is different from using the disp function. You should NOT use both in a function! Show the output argument in your diary file.

Explanation / Answer

If angle of incidence is maintained, this implies that lift coefficient in turn CL,t is the same as lift coefficient in straight-level flight, viz, CL,t = CL,s. Thus, Vt = NVs. Since the drag coefficient is determined by the lift coefficient, the drag coefficient in turning flight is therefore the same as in straight level flight. In straight level flight

nt in turning flight is therefore the same as in straight level flight. In straight level flight Ts = Ds = 1 2 SCDV 2 s Thus in turning flight

Tt = Dt = 1 2 SCDV 2 t = 1 2 SCDNV 2 s = DsN

Hence thrust must be increased by a factor of N compared to straight level flight.

Turn rate in rad/s is = 2 1 15 Air density found from = 0 = 0
Hence = 1.136.

Next, note that WL = m/S, and also that same incidence angle implies CL,s = CL,t

so CL can be calculated as CL = q2gWL V 2 s = 10.36

Related Questions

Navigate

• Browse (All)
• Browse P
• Subjects

---

---

Integrity-first tutoring: explanations and feedback only — we do not complete graded work. Learn more.