Answer Happy

3. For an aircraft in a steady horizontal turn the following data, as indicated in the table below, is given. W S h P [kg/m³] [kN] [m²] [m] 77.2 30.4 1000 1.1117 [5 pt.] Calculate: ● radius of curvature R, ● bank angle , ● load factor n turning time T₂T Pbr [kW] 1110 ПР [-] 0.69 V [km/u] 412 Соо 0.0163 8.26 A H e 0.75

3 Please, please do NOT use L-W! remember that we are in a turn where lift does NOT equal weight. Also the conditions are given and they are not at (L/D)_max. (If you use any of these assumptions you will score ZERO points for this question!) So first from T-D determine C_D=0.0302 then from the drag polar it follows that: C_L=0.521 and subsequently: phi = 48.0deg n=1.49 R=1204m omega=0.095rad/s T_2Pl=66s