An investigation of inviscid transonic flow over a flattened airfoil whose curvature is small in the midchord region is performed. Numerical simulation reveals a bifurcation of steady solutions to the Euler equations in a range of freestream Mach numbers M_∞ and angles of attack α. The dependence of the lift coefficient C_L on M_∞ and α is studied in the intervals -1.2 < α, deg < 1.2, 0.79 < M_∞ < 0.85. A theoretical interpretation of the bifurcation and instability phenomena is presented.