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absolute coefficient accelerated aerodynamic Aeronautical ahead airfoil surface analysis angle of attack apply aspect ratio axis caused Cleveland consideration constant contributed corresponding determined dihedral direction Director disturbance drag edge effect equation expression Field flight flow formulas function give given in table inclination indicated induced integration John Kutta-Joukowski condition Laboratory lateral lift linearized longitudinal Mach cone MACH LINES Mach number means midchord point moment moments motions negative normal obtained origin pitching plan forms positive potential present pressure coefficient pressure distribution previously principal body axes produced rectangular wing reference region relative respect rolling satisfied shows sideslip skin friction solutions span stability axes stability derivatives steady stream Mach number suction forces supersonic speeds surface SYMBOLS Theoretical theory thin flat tion tip Mach tip section trailing wing tip transformation Triangular unit unsteady motions various vertical motion yawing zero
Page 11 - 5. Ribner, Herbert S.: The Stability Derivatives of Low-AspectRatio Triangular Wings at Subsonic and Supersonic Speeds. NACA TN 1423, 1947.
Page 11 - Moeckel, WE: Effect of Yaw at Supersonic Speeds on Theoretical Aerodynamic Coefficients of Thin Pointed Wings with Several Types of Trailing Edge. NACA TN 1549,