Zastosowanie metody linii Macha do wyznaczania naddźwiękowego opływu skrzydeł o dowolnym obrysie

A method is discussed for calculating the disturbed velocity potential in staedy supersonic flow over wings. The methods of the theoretical aerodynamics have benn here adapted to practical computation. The method derived is called the Mach-line method and can be applied for calculation of aerodynamc coefficients independently of the aerodynamic design of an aircraft.