Page 41 - Aerodynamics for Engineering Students
P. 41

24  Aerodynamics for Engineering Students
                     From the figures given above, the Reynolds number VDp/p may be calculated for each case.
                   These are found to be
                              Case (A)   Re = 5.52 x lo7   Case (D)   Re = 7.75 x lo6
                              Case (B)   Re = 1.84 x lo7   Case (E)   Re = 5.55 x lo7
                              Case (C)   Re = 5.56 x lo7   Case (F)   Re = 1.11 x lo8

                     It is seen that the values of Re for cases (C) and (E) are very close to that for the full-size
                   aircraft. Cases (A), (C) and (E) are therefore dynamically similar, and the flow patterns in these
                   three cases will be geometrically similar. In addition, the ratios of the local velocity to the free
                   stream velocity at any point on the three bodies will be the same for these three cases. Hence,
                   from Bernoulli's equation, the pressure coeficients will similarly be the same in these three
                   cases, and thus the forces on the bodies will be simply and directly related. Cases (B) and @)
                   have Reynolds numbers considerably less  than  (A), and are, therefore, said to represent a
                   'smaller aerodynamic scale'.  The flows around these models, and the forces acting on them,
                   will not be simply or directly related to the force or flow pattern on the full-size aircraft. In case
                   (F) the value of Re is larger than that of any other case, and it has the largest aerodynamic scale
                   of the six.
                   Example 1.2  An aeroplane approaches to land at a speed of 40 m s-l  at sea level. A  1/5th
                   scale model is tested under dynamically similar conditions in a Compressed Air Tunnel (CAT)
                   working at 10 atmospheres pressure and  15°C. It is found that the load on the tailplane is
                   subject to impulsive fluctuations at a frequency of 20 cycles per second, owing to eddies being
                   shed  from the wing-fuselage junction.  If  the natural  frequency of  flexural vibration of  the
                   tailplane is 8.5 cycles per second, could this represent a dangerous condition?
                     For  dynamic similarity, the  Reynolds numbers must be equal.  Since the temperature of
                   the atmosphere equals that in the tunnel, 15 "C, the value of p is the same in both model and
                   full-scale cases. Thus, for similarity

                                                vfdfpf  = Vm4nfi
                   In this case, then, since
                                                 Vf  =mms-'
                                                          1
                                          40x 1 x 1 = v,  x-x  1o=2vm
                                                         5
                   giving


                   Now Eqn (1.38) covers this case of eddy shedding, and is

                                                   nd
                                                   - = g(Re)
                                                   V
                   For dynamic similarity




                   Therefore



                   giving                      nf = 8 cycles per second
   36   37   38   39   40   41   42   43   44   45   46