1 Landing Analysis for Airbus A320-200 4320 FIGURE 1:A320-200. A320 AIRBUS Introduction: hOBSTACLE ya Sa APPROACH DISTANCE 2 R Main Objective: Y₂ R TOUCH DOWN BRAKES V=VTD APPLIED SF FLARE

DISTANCE L... SB SFR FREE BRAKING ROLL DISTANCE GROUND ROLL TOTAL LANDING DISTANCE The start and end of a flight are represented by the take-off and landing of an aircraft. These procedures can be performed from various locations all around the world, depending on the weather and humidity. An airplane takes off at its maximum weight, but it lands with less weight due to its fuel consumption. In order to ensure the safety of the passengers and crew, the pilot must manually control the aircraft. FIGURE 2: TAKE-OFF DRAWING (FRICKE, 2015) The latest version of the certification specifications for large transport airplanes is regularly published by the various aviation authorities. This guide is used by manufacturers to ensure that their aircrafts are safe. In this section, an analysis of the procedures related to the landing operations of an Airbus A320 was performed and compared with the published data. The main objective is to analyse the Landing operation for A320-200 Calculations: All the parameters used to do the procedure of the analysis is shown in table 1 below: Parameter Value Unit Source p/p sls P K S MLW W/S CL max landing CDO CDO undercarriage CDO high lift CDO total BPR Tsls/W u H obstacle S spoilers S spoilers / S y min Landing stall 3 Landing stall Landing stall = = 2 (W/S) Landing Lmax pC 2 * 5289.706 1.225 * 2.63 1 = 57.304 m/s 1.225 0.055956 122.4 66000 5289.706 2.63 0.018072117 0.02081058 0.025323149 0.064133729 5.7 To perform the analysis a certain steps are required: To find the steepest approach angle: 0.324037507 0.05 15.24 8.64 0.070588235 0.024 kg/m^2 m² kg N/m^2 3 Lecture notes Standard sea level value ADE Lecture notes first section All Janes All Janes Calculated from previous reports ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section WIKI Altitude-Speed report ADE Lecture notes first section ADE Lecture notes first section All Janes Calculated ADE Lecture notes TABLE 1: A320-200 PARAMETERS. [1] Va = 1.3 Landing stall Va Va = 74.495m/s CL CL = 1.3 * 57.304 T W CL = 1.556 (W/S) ZPVZ 5289.706 * 1.225 * 74.495² CD = Com + Chigh lift Cp = 0.064133729 +0.055956 * 1.556² CD = 0.1996 Ya cruise -sinya 4 = 0.2- undercarrige + Co T = 0.2 0.32404 * 1 = 0.064808 W DO sls-max P W Psls -sinya = 0.064808- -sinya 1 T W CL/CD 1 1.556/0.1996 = -0.0634696 Radians 0.0634696Rad = 3.639 Degrees VF = 1.23 Landing stall VF = 1.23 * 57.304 VF = 70.4839 m/s To find the flare segment : +KC [5] [6] [2] [3] [7] [4] 0.2g 70.4839² 0.2 * 9.81 R = 2532.1 m R = hƑ = R(1 − cosya) hF = 2532.1(1 − cos(3.639)) = 5.105 m SF = R(sinya) SF = = 2532.1(0.06346)=160.7 m SA SA = 'DO The approach segment ΚΑ 5 hobstacle - hf tanya 15.24 5.105 tan (3.639) VTD = VTD = 1.15* 57.304 = 65.8996 m/s SFR = 2VTD SFR = 2 * 65.8996 = 131.7992 m Free rolling segment : 1.15vLanding stall Spoilers Case NO.1: Dry runway CSpoilers 159.36 m Ground roll with thrust reversers and dry runway: = 1.6 Spoiler frontal area S = 1.6 * 0.070588235 = 0.112941176 PCDO 2(W/S) [8] [10] [9] [11] [12] [13] [14] [15]/n Take-off Analysis for Airbus A320-200 4320 FIGURE 1:A320-200. 1 A320 AIRBUS Introduction: True Airspeed (TAS) Cimb Angle (y) Rate of Climb (ROC) ROC = TAS * sin y Takeoff Run (Flaps 15) Liftoff Flaps 15° Takeoff Run (Flaps 0) Main Objective: TAS ROC Initial Climb FIGURE 2: TAKE-OFF DRAWING (FRICKE, 2015) Liftoff 2 TAS Flaps 0° The start and end of a flight are represented by the take-off and landing of an aircraft. These procedures can be performed from various locations all around the world, depending on the weather and humidity. An airplane takes off at its maximum weight, but it lands with less weight due to its fuel consumption. In order to ensure the safety of the passengers and crew, the pilot must manually control the aircraft. The main objective is to analyse the take-off operation for A320-200 Initial Climb The latest version of the certification specifications for large transport airplanes is regularly published by the various aviation authorities. ROC This guide is used by manufacturers to ensure that their aircrafts are safe. In this section, an analysis of the procedures related to the take-off operations of an Airbus A320 was performed and compared with the published data. Calculations: All the parameters used to preform the procedure of the analysis is shown in table 1 below: Parameter Value Unit Source p/p sls P K S MTOW W/S CL max T-O CDO CDO undercarriage CDO high lift CDO total BPR Tsls/W u H obstacle y min Cundercarriage 'DO Cundercarriage 'DO Cundercarriage 'DO Ccruise high-lift DO Chigh-lift - 0.018 = Kuc = 0.02313 1 1.225 0.047914014 122.4 75500 6051.102941 2.23 To perform the analysis a certain steps are required: Finding the coefficient for take off m 0.785 S 0.095x75.50.785 122.4 0.018072117 0.0234875 0.014470371 0.056029988 5.7 0.324037507 0.05 10.7 0.024 kg/m^2 = K, (Chap) (Snapped) (8 - 10) 0.0074x0.133x (0.735133) (30 – 10) m² kg N/m^2 m Lecture notes Standard sea level value ADE Lecture notes first section All Janes All Janes Calculated from previous reports ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes first section WIKI TABLE 1: A320-200 PARAMETERS. 3 Altitude-Speed report ADE Lecture notes first section ADE Lecture notes first section ADE Lecture notes [1] [2] high-lift 'DO Ctotal DO K = K = ΚΑ ΚΑ ΚΑ = Кт Кт 1.43 TAR 1.43 π * 9.5 = 0.014470 = 0.05603 - VTO VTO VTO = -5.574 * 10-6 = 0.75 Case No.1: Take-off distance on a dry runway: To find ground roll segment: PC DO 2 (W/S) 1.225 * 0.055 2(6051.103) KŢ = 0.75 0.32404 * 1 * = 0.218 = = Vtake-off stall = 0.047914 vtake-off stall take-off stall Tsls- sls-max P 5 + BPR W Psl 4+ BPR = To find the transition to stabilised climb speed: 2 (W/S) take-off 'Lmax pct 2 6051.1029 1.225 * 2.23 = 66.5598 m/s /5 +5.7 4+ 5.7/ 1.1vtake-off stall 1.1 * 66.5598 73.2157 m/s μ 0.05 4 [3] [4] [5] [6] [7] SG SG SR V TR SG = 1347.396 m V TR VTR SR = 3V TO SR = 3 * 73.2157 R = - R = T W CL = 219.647 m CL 1 2gKA To find the ground roll: K₁ + KAVTO T Кт = 1 2 * 9.818 * (-5.574 * 10¯6) = In - = C₁ = = 1.15 * 66.5598 76.543732² 0.2 * 9.81 R = 2986.2 m Since the time rotate to take-off is 3 seconds so the distance covered during rotation is: To find the transition segment: 1.15vtake-off stall 76.54377 m/s VFR TR 0.2g To find the radius of curvature: Tsls-max W (W/S) 1 In TR (0.21808 + (−5.726 * 10-6)* 73.2157² 0.21808 = 0.32404 To find the lift and drag coefficient during transition: 6051.102 * 1.225 * 76.54377² 2 = 1.6862 [8] 5 [10] [11] [12] [13]