(b) Determine the drag and lift coefficients for values of the AOA V=0 CDN-> e The...

 

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(b) Determine the drag and lift coefficients for values of the AOA V=0 CDN-> e The inverted supersonic delta wing corresponding to the specific drawing above is considered to be the zero angle of attack (AOA) orientation with the upstream top panel of the delta wing parallel to the incoming supersonic flow. The length of the top plate (also known as the chord length) is equal to C = 0.1 m. The dimensionless drag and lift coefficients (CD and Cz) are defined as: CD 1 FD PVC and C = FL 1 PVC with FD, FL, P and V being the drag force per unit width into paper, lift force per unit width into paper, density of air approaching the wing and the velocity of air approaching the delta wing, respectively. The CD and CL values for AOA = 0 and 5 (clockwise) are given in the table 1. At the outset, make a drawing of the new orientation of the delta wing. (b) Determine the drag and lift coefficients for values of the AOA V=0 CDN-> e The inverted supersonic delta wing corresponding to the specific drawing above is considered to be the zero angle of attack (AOA) orientation with the upstream top panel of the delta wing parallel to the incoming supersonic flow. The length of the top plate (also known as the chord length) is equal to C = 0.1 m. The dimensionless drag and lift coefficients (CD and Cz) are defined as: CD 1 FD PVC and C = FL 1 PVC with FD, FL, P and V being the drag force per unit width into paper, lift force per unit width into paper, density of air approaching the wing and the velocity of air approaching the delta wing, respectively. The CD and CL values for AOA = 0 and 5 (clockwise) are given in the table 1. At the outset, make a drawing of the new orientation of the delta wing.