@article{oai:jaxa.repo.nii.ac.jp:00034373,
 author = {KARASHIMA, Keiichi},
 issue = {1},
 journal = {ISAS report/Institute of Space and Aeronautical Science,University of Tokyo},
 month = {Jan},
 note = {A study of plane and axially symmetric supersonic flow is made for the approximate inviscid theory of such comparatively thick bodies that the linearized equation does not adequately predict an essential feature of flow. The second-order small disturbance equations are derived for plane and axially symmetric motions involving shock waves and the range of applicability is shown from order estimation of the error involved in the approximation. For very high supersonic Mach numbers it is shown that the present approach is reduced to the first-order hypersonic small disturbance theory proposed by Van Dyke and, there fore, a single small disturbance theory may predict the flow at all supersonic speeds above the trasonic. Several examples are numerically calculated for two-dimensional biconvex circular-arc airfoils, cones and a paraboloid-arc half-body of revolution with respect to their surface pressure distribution and initial shock wave curvature, etc., and compared with full solutions and other approximate solutions when available. Experimental measurement of surface pressure distribution and observation of shape of the shock wave are made for a paraboloid-arc half-body of revolution with fineness ratio of 6.693 and for Mach numbers of 2,3 and 8,and the results are compared with those of the present theory and others. It is concluded that the present theory agrees well with the method of characteristics and the experimental results also confirm the present approach., 資料番号: SA2400490000},
 pages = {1--49},
 title = {Second-Order Supersonic Small Disturbance Theory},
 volume = {30},
 year = {1965}
}