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Flight Investigation at High Mach Numbers of Several Methods of Measuring Static Pressure on an Airplane Wing

出版	National Advisory Committee for Aeronautics, 1944
URL	http://books.google.com.hk/books?id=qm4hrsE0eCMC&hl=&source=gbs_api
EBook	FULL_PUBLIC_DOMAIN

註釋Summary: A flight investigation was made to compare static pressures in subsonic and supersonic flow over an airplane wing as measured by static-pressure tubes, a static-pressure belt, and orifices flush with the wing surface. The measurements were made on the upper surface of the wing of the P-47D airplane over a range of flight conditions in which local Mach numbers from 0.34 to 1.41 were obtained at the measurement stations. For some of the tests, a total-pressure tube was mounted on the wing surface to determine its characteristics in supersonic flow. The results indicated that static-pressure measurements obtained with suitably designed and installed flush orifices, static-pressure tubes, and static-pressure belt will be in reasonable agreement for both subsonic and supersonic flow. The pressures in supersonic flow measured by the total-pressure tube mounted on the wing surface were found to be in close agreement with values predicted by theory.