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Diffstat (limited to '797/CH11/EX11.5s/11_05_solution.sce')
| -rw-r--r-- | 797/CH11/EX11.5s/11_05_solution.sce | 30 |
1 files changed, 30 insertions, 0 deletions
diff --git a/797/CH11/EX11.5s/11_05_solution.sce b/797/CH11/EX11.5s/11_05_solution.sce new file mode 100644 index 000000000..b00d31a87 --- /dev/null +++ b/797/CH11/EX11.5s/11_05_solution.sce @@ -0,0 +1,30 @@ +//Solution 11-5 +WD=get_absolute_file_path('11_05_solution.sce'); +datafile=WD+filesep()+'11_05_example.sci'; +clc; +exec(datafile) +//unit conversions +V = V / 3.6; //from [km/h] to [m/s] +//(a) +W = m * g; //weight of aircraft [N] +//from total weight = lift force minimum velocity is given by +V_min1 = sqrt(2 * W /(rho_ground * C_Lmax * A)); +V_min2 = sqrt(2 * W /(rho_ground * C_Lmax_flap *A)); +V_min1_safe = 1.2 * V_min1; //safe velocity without flaps +V_min2_safe = 1.2 * V_min2; //safe velocity with flaps +V_min1_safe = V_min1_safe * 3.6; //from [m/s] to [km/h] +V_min2_safe = V_min2_safe * 3.6; //from [m/s] to [km/h] +printf("a) The minimum safe speed for landing and takeoff are\n"); +printf ("\t %1.0f km/h without flaps\n", V_min1_safe); +printf("\t %1.0f km/h with flaps\n", V_min2_safe); +//(b) +C_L = W / (0.5 * rho_altitude * V**2 * A); +//from figure 11-45 the angle of attack corresponding to above C_L value is +alpha = 10; +printf("b) The angle of attack to cruise steadily at crusing altitude is %1.0f degrees.\n", alpha); +//(c) +//from figure 11-45 drag coefficient corresponding to C_L is +C_D = 0.03; +F_D = C_D * A * rho_altitude * V**2 / 2; //thrust force = drag force +P = F_D * V; //power required to provide thrust +printf("c) The power that needs to be supplied to provide enough thrust is %1.0f kW.", P / 1000); |