Definition of Cutting Planes for CRM-HL, Version 1 Note that the pressure taps on the model's wing are aligned on all 3 elements only when the configuration is stowed. When in the deployed position, you must make a separate "cut" on each of the elements according to the following formula (for each of the 7 span stations): AX + BY + CZ = D Section A B C D Slat A 0.104119929 0.954339262 -0.279992165 238.2211 B 0.104119929 0.954339262 -0.279992165 341.2211 C N/A D 0.098554005 0.951600458 -0.291107671 537.5779 E 0.098554005 0.951600458 -0.291107671 692.0779 F 0.098554005 0.951600458 -0.291107671 846.5779 G 0.098554005 0.951600458 -0.291107671 1001.0779 H 0.098554005 0.951600458 -0.291107671 1104.0779 Main-wing A 0 1 0 174.5 B 0 1 0 277.5 C 0 1 0 380.5 D 0 1 0 483.5 E 0 1 0 638.0 F 0 1 0 792.5 G 0 1 0 947.0 H 0 1 0 1050.0 Flap (Nominal Configuration 40/37) A -0.072048275 0.984234043 0.161531403 93.1704 B -0.072048275 0.984234043 0.161531403 196.1704 C -0.072048275 0.984234043 0.161531403 299.1704 D 0.029643949 0.939303397 0.34180457 568.1416 E 0.029643949 0.939303397 0.34180457 722.6416 F 0.029643949 0.939303397 0.34180457 877.1416 G N/A H N/A Flap (Configuration 37/34) A -0.069908414 0.986380926 0.148880769 94.7539 B -0.069908414 0.986380926 0.148880769 197.7539 C -0.069908414 0.986380926 0.148880769 300.7539 D 0.018626895 0.947755364 0.318453779 550.8612 E 0.018626895 0.947755364 0.318453779 705.3612 F 0.018626895 0.947755364 0.318453779 859.8612 G N/A H N/A Flap (Configuration 43/40) A -0.073536649 0.981952471 0.174246107 92.4997 B -0.073536649 0.981952471 0.174246107 195.4997 C -0.073536649 0.981952471 0.174246107 298.4997 D 0.041625338 0.930435683 0.364083467 586.4414 E 0.041625338 0.930435683 0.364083467 740.9414 F 0.041625338 0.930435683 0.364083467 895.4414 G N/A H N/A