\$Revision: 1.0\$ This is CL basic data for Boeing 747-100 for 3 flap settings and a range of angles of attack. It comes from NASA CR 114494 page 2.0-7. This is only a small subset of the data created for testing the 2D ungridded tabular data in DAVE-ML. It was created by Peter Grant from the University of Toronto Novemember 1, 2006. Revision 1.0: Initial checkin. Rearranged slightly to conform to DTD 1.9. Corrected PUBLIC ID and added default namespace per DTD 2.0RC3 change; changed no dimension abbreviation from ND to nd per draft 2 AIAA S-119 document. Offset of design plane of wing relative to body axis Trailing edge flap deflection in degrees +DOWN Angle of attack of design wing plane in degrees +ANU $\mathrm{angleOfAttack_d}+\mathrm{alpha0}$ Calculate the 747-100 basic lift coefficient. This only includes effects for flaps and angle of attack. This is only a small subset of actual aircraft data. CL basic as a function of flap angle and angle of attack. Note the alpha used in this table is with respect to the wing design plane (in degrees). Flap is in degrees as well. 15 1.0 -5.00 -0.44 1.0 10.00 0.95 1.0 12.00 1.12 1.0 14.00 1.26 1.0 15.00 1.32 1.0 17.00 1.41 5.0 -5.00 -0.55 5.0 0.00 -0.03 5.0 5.00 0.50 5.0 10.00 1.02 5.0 12.00 1.23 5.0 14.00 1.44 5.0 16.00 1.63 5.0 17.00 1.70 5.0 18.00 1.75 10.0 -5.00 -0.40 10.0 14.00 1.57 10.0 15.00 1.66 10.0 16.00 1.75 10.0 17.00 1.80 10.0 18.00 1.84 angleOfAttack_d -2. flapdef 1. CLBASIC 0.0233 0.0005 angleOfAttack_d 0.5 flapdef 2.5 CLBASIC 0.2600 0.0001 angleOfAttack_d 1.6 flapdef 6.0 CLBASIC 0.3822 0.0001 angleOfAttack_d 7.1 flapdef 8.0 CLBASIC 1.0072 0.0001