The heat transfer characteristics of annular fin and tube radiators have been determined analytically. The complex interaction problem resulting from mutual irradiation between neighboring fins and between fins and the tube surface has been fully accounted for by applying a newly-devised contour-integral method for deriving the radiant interchange factors. The mathematical description of the simultaneous heat transport by conduction and radiation leads to a nonlinear integro-differential equation. This has been solved for a wide range of the pertinent physical parameters. The heat transfer from the fin-tube system has been calculated and is presented graphically in dimensionless form. The separate contributions to the total of the fin and of the tube are also shown. The results definitely indicate that the use of fins leads to a significant increase in heat transfer compared with the unfinned tube.
{"title":"Radiating Effectiveness of Annular-Finned Space Radiators, Including Mutual Irradiation Between Radiators Elements","authors":"E. Sparrow","doi":"10.2514/8.9797","DOIUrl":"https://doi.org/10.2514/8.9797","url":null,"abstract":"The heat transfer characteristics of annular fin and tube radiators have been determined analytically. The complex interaction problem resulting from mutual irradiation between neighboring fins and between fins and the tube surface has been fully accounted for by applying a newly-devised contour-integral method for deriving the radiant interchange factors. The mathematical description of the simultaneous heat transport by conduction and radiation leads to a nonlinear integro-differential equation. This has been solved for a wide range of the pertinent physical parameters. The heat transfer from the fin-tube system has been calculated and is presented graphically in dimensionless form. The separate contributions to the total of the fin and of the tube are also shown. The results definitely indicate that the use of fins leads to a significant increase in heat transfer compared with the unfinned tube.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134094944","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
prompted the consideration of other techniques. One alternate or perhaps interim approach presently being considered is that of establishing the average values of inlet performance in such an environment by means of force-balance measurements of the internal drag of these inlets. Such performance data can be used to determine where (for families of arbitrary inlet con figurations) a particular inlet's operating point will be on para metric inlet-performance curves similar to those in Fig. 1. Such experimental data also afford a relatively simple means of evalu ating the end effects of hypersonic shock, boundary-layer inter action, and inlet boundary-layer separation phenomena on the performance levels of such inlets. In addition, these average values of inlet performance can be used as a basis for supporting combustor and nozzle performance calculations, thus permitting estimation of the complete propulsion-system performance. This note presents the results of a preliminary investigation of the accuracy to be expected from computed values of inlet performance based on force-balance measurements of inlet drag. For purposes of discussion here, the two basic parameters neces sary to specify the performance of supersonic/hy personic com bustion inlets—i.e., diffusion efficiency and degree of diffusion— are considered to be the familiar inlet total-pressure recovery and the inlet static-pressure ratio, respectively. Inlet total-pressure recovery, among other things, is indicative of inlet-area dis tribution, and aside from combustion considerations, inlet static-pressure rise is an index of viscous problems associated with the diffusion process. Assuming that the internal drag of the model can be ade quately isolated from other model drag values, and assuming that
{"title":"Effect of Wing Geometry on Volume and Weight","authors":"B. Saelman","doi":"10.2514/8.9828","DOIUrl":"https://doi.org/10.2514/8.9828","url":null,"abstract":"prompted the consideration of other techniques. One alternate or perhaps interim approach presently being considered is that of establishing the average values of inlet performance in such an environment by means of force-balance measurements of the internal drag of these inlets. Such performance data can be used to determine where (for families of arbitrary inlet con figurations) a particular inlet's operating point will be on para metric inlet-performance curves similar to those in Fig. 1. Such experimental data also afford a relatively simple means of evalu ating the end effects of hypersonic shock, boundary-layer inter action, and inlet boundary-layer separation phenomena on the performance levels of such inlets. In addition, these average values of inlet performance can be used as a basis for supporting combustor and nozzle performance calculations, thus permitting estimation of the complete propulsion-system performance. This note presents the results of a preliminary investigation of the accuracy to be expected from computed values of inlet performance based on force-balance measurements of inlet drag. For purposes of discussion here, the two basic parameters neces sary to specify the performance of supersonic/hy personic com bustion inlets—i.e., diffusion efficiency and degree of diffusion— are considered to be the familiar inlet total-pressure recovery and the inlet static-pressure ratio, respectively. Inlet total-pressure recovery, among other things, is indicative of inlet-area dis tribution, and aside from combustion considerations, inlet static-pressure rise is an index of viscous problems associated with the diffusion process. Assuming that the internal drag of the model can be ade quately isolated from other model drag values, and assuming that","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"100 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117236427","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Summary The equations to be represented in the computer of an inertial navigation system for use near the surface of the earth are derived by elementary methods, and a block diagram of the computer is presented. No restrictions are placed on the nature of the earth's gravity field and only minor restrictions on the shape of the earth. The shape and gravity field of the earth are dis cussed and specialization of the equations and block diagram is made for the case where the earth and gravity field are assumed to have axial symmetry.
{"title":"Elementary Derivation of General Equations for Terrestrial Inertial Navigation","authors":"O. T. Schultz","doi":"10.2514/8.9806","DOIUrl":"https://doi.org/10.2514/8.9806","url":null,"abstract":"Summary The equations to be represented in the computer of an inertial navigation system for use near the surface of the earth are derived by elementary methods, and a block diagram of the computer is presented. No restrictions are placed on the nature of the earth's gravity field and only minor restrictions on the shape of the earth. The shape and gravity field of the earth are dis cussed and specialization of the equations and block diagram is made for the case where the earth and gravity field are assumed to have axial symmetry.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116983777","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"A Note on the Similarity Solution for the Three-Dimensional, Incompressible, Laminar Boundary Layer","authors":"A. Ray","doi":"10.2514/8.9831","DOIUrl":"https://doi.org/10.2514/8.9831","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"27 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115015149","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
REFERENCES 1 Mindlin, R. D., and Goodman, L. E., Beam Vibrations with TimeDependent Boundary Conditions, J. Appl. Mech., Vol. 17, pp. 377-380, Dec. 1950. 2 Timoshenko, S. P., and Woinowsky-Krieger, S., Theory of Plates and Shells, 2nd Ed., p. 113; McGraw-Hill Book Co., Inc., New York, 1959. 3 Boley, B. A., and Weiner, J. H., Theory of Thermal Stresses, pp. 402-404; John Wiley and Sons, Inc., New York, 1960.
参考文献 1 Mindlin, R. D., and Goodman, L. E., Beam Vibrations with TimeDependent Boundary Conditions, J. Appl. Mech., Vol. 17, pp.2 Timoshenko, S. P., and Woinowsky-Krieger, S., Theory of Plates and Shells, 2nd Ed., p. 113; McGraw-Hill Book Co., Inc., New York, 1959.3 Boley, B. A., and Weiner, J. H., Theory of Thermal Stresses, pp.
{"title":"Couette-Type Flow of a Viscoelastic Fluid Through Porous Walls","authors":"P. Kaloni","doi":"10.2514/8.9841","DOIUrl":"https://doi.org/10.2514/8.9841","url":null,"abstract":"REFERENCES 1 Mindlin, R. D., and Goodman, L. E., Beam Vibrations with TimeDependent Boundary Conditions, J. Appl. Mech., Vol. 17, pp. 377-380, Dec. 1950. 2 Timoshenko, S. P., and Woinowsky-Krieger, S., Theory of Plates and Shells, 2nd Ed., p. 113; McGraw-Hill Book Co., Inc., New York, 1959. 3 Boley, B. A., and Weiner, J. H., Theory of Thermal Stresses, pp. 402-404; John Wiley and Sons, Inc., New York, 1960.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130775296","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Wing-Tail Interference as a Cause of \"Magnus\" Effects on a Finned Missile","authors":"E. R. Benton","doi":"10.2514/8.9813","DOIUrl":"https://doi.org/10.2514/8.9813","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"115 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133507775","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"Thermal Bending of Rectangular Plate","authors":"Y. C. Das","doi":"10.2514/8.9839","DOIUrl":"https://doi.org/10.2514/8.9839","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123833432","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The variational principle of minimum potential energy is used to determine the deflections and stresses of a flat isotropic sandwich beam with freely sliding clamped ends when subjected to symmetrical lateral loads and end axial forces. Expressions are obtained for the cases of tensile, compressive, and no axial load, acting together with a general symmetrical transverse loading. Curves for the nondimensional deflections and stresses are presented for a uniformly loaded sandwich beam coupled with axial load as functions of two structural parameters. A representative numerical example showing the application of the curves is also given.
{"title":"Deflections and Stresses of a Clamped Rectangular Sandwich Beam","authors":"T. Fang","doi":"10.2514/8.9814","DOIUrl":"https://doi.org/10.2514/8.9814","url":null,"abstract":"The variational principle of minimum potential energy is used to determine the deflections and stresses of a flat isotropic sandwich beam with freely sliding clamped ends when subjected to symmetrical lateral loads and end axial forces. Expressions are obtained for the cases of tensile, compressive, and no axial load, acting together with a general symmetrical transverse loading. Curves for the nondimensional deflections and stresses are presented for a uniformly loaded sandwich beam coupled with axial load as functions of two structural parameters. A representative numerical example showing the application of the curves is also given.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"102 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115177147","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
{"title":"On the Crack-Tip Stress-Intensity Factors for Cylindrical Bars Under Torsion","authors":"G. Sih","doi":"10.2514/8.9776","DOIUrl":"https://doi.org/10.2514/8.9776","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"4 4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129311328","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A PREVIOUS PAPER 1 discussed the theory of the elastic and plastic behavior of wings and other beam-type control surfaces. This early work used a modal-type approach for both the elastic and post-failure regions. A great deal of study has been devoted to the problem since this early work and it has been found more efficient to employ a finite-difference technique to solve both the elastic and elasto-plastic cases. The equations of motion together with the boundary and continuity conditions for a variable-section beam or control surface are given in a previous reference. The finite-difference equations are given in general form for fixed, simply supported, free, and plastic-hinged beams in another report.
{"title":"Plastic Behavior of Beam-Type Structures","authors":"J. Greenspon","doi":"10.2514/8.9767","DOIUrl":"https://doi.org/10.2514/8.9767","url":null,"abstract":"A PREVIOUS PAPER 1 discussed the theory of the elastic and plastic behavior of wings and other beam-type control surfaces. This early work used a modal-type approach for both the elastic and post-failure regions. A great deal of study has been devoted to the problem since this early work and it has been found more efficient to employ a finite-difference technique to solve both the elastic and elasto-plastic cases. The equations of motion together with the boundary and continuity conditions for a variable-section beam or control surface are given in a previous reference. The finite-difference equations are given in general form for fixed, simply supported, free, and plastic-hinged beams in another report.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"132 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1962-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131712256","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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