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Wind-tunnel Tests in Connection with Stabilization of Projectiles with Control Surfaces Held to Size of One Caliber at Supersonic Speed
O. Walchner
出版Wright Field, Air Materiel Command, 1948
URLhttp://books.google.com.hk/books?id=mXZntwAACAAJ&hl=&source=gbs_api
註釋By means of three-component measurements in wind tunnel at Mach numbers of 1.45, 1.99, and 2.64, course-of-drag coefficient, normal-force coefficient, and pressure-point position were determined with angles of attack ranging up from 6 degrees. Use of fir-cone tip to improve pressure-point position is discussed.