A numerical integration method for calculating the pressure distribution at supersonic speeds for wings with subsonic leading edge at symmetrical flow conditions
By: V. V. Linnaluoto.
Contributors: Saab Aircraft Company
Series: Saab Aircraft Company. Technical notes -- 6
Publisher: Saab Aircraft Company
Published: 1951
Place of publication: Linkoping, Sweden
Number of pages: 19
Notes: Bibliographical references: p. 8-9.