To provide a supersonic type aircraft configuration capable of solving a problem of a trim held by a conventional cross section area distribution of George and Seebass and attaining a rear end low sonic boom even if a horizontal stabilizer of usual wing back arrangement is adopted.

In the machine body shape of the supersonic type aircraft, equivalent cross section area distribution, i.e., the sum of machine body axial direction distribution of a cross section obtained by cutting the machine body shape by Mach plane determined by flying Mach number and a cross section area distribution obtained by converting machine axial direction distribution of lift to cross section area distribution equivalent to it has distribution having the maximum value on the midway without monotonously increasing it in the machine axial direction, and is provided with a portion where the equivalent cross section area is increased again without monotonously reducing it in the process that the equivalent cross section area is reduced from a position for taking the maximum value to a rear end of the machine body.