{"title":"Analytical and Numerical Studies of Three-Dimensional Trajectories to the Moon","authors":"A. B. Mickelwait, R. Booton","doi":"10.2514/8.8653","DOIUrl":"https://doi.org/10.2514/8.8653","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133447512","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 Optimum Nose Shapes for Missiles in the Superaerodynamic Region","authors":"I. Chang","doi":"10.2514/8.7486","DOIUrl":"https://doi.org/10.2514/8.7486","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124014551","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 Perturbation Analysis of Shock Flow in a Nozzle","authors":"R. Gundersen","doi":"10.2514/8.8299","DOIUrl":"https://doi.org/10.2514/8.8299","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129806092","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":"Maneuvering Technique for Changing the Plane of Circular Orbits With Minimum Fuel Expenditure","authors":"David C. Weiss","doi":"10.2514/8.9451","DOIUrl":"https://doi.org/10.2514/8.9451","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124960555","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}
An analysis is made of the second-order effects of thickness on the unsteady aerodynamic forces on a slender pointed body of revolution in supersonic flow. The theory is restricted to harmonic oscillations for small angles of attack. The solution is obtained by approximating the nonlinear terms in the second-order potential equation by their first-order values and solving the resulting inhomogeneous partial differential equation, subject to more refined boundary conditions. The pressure equation is likewise refined and integrated to give the second-order corrections to lift and pitching moment coefficients. The analysis can be considered as an extension of the second-order, slender body theory of Lighthill to the case of unsteady flow. The results indicate appreciable reductions in unsteady lift and damping moment coefficients when applied to slender cones. The present theory is estimated to be reliable provided that Mb is less than 0.7.
{"title":"Second-Order Theory for Unsteady Supersonic Flow Past Slender, Pointed Bodies of Revolution","authors":"J. Revell","doi":"10.2514/8.8739","DOIUrl":"https://doi.org/10.2514/8.8739","url":null,"abstract":"An analysis is made of the second-order effects of thickness on the unsteady aerodynamic forces on a slender pointed body of revolution in supersonic flow. The theory is restricted to harmonic oscillations for small angles of attack. The solution is obtained by approximating the nonlinear terms in the second-order potential equation by their first-order values and solving the resulting inhomogeneous partial differential equation, subject to more refined boundary conditions. The pressure equation is likewise refined and integrated to give the second-order corrections to lift and pitching moment coefficients. The analysis can be considered as an extension of the second-order, slender body theory of Lighthill to the case of unsteady flow. The results indicate appreciable reductions in unsteady lift and damping moment coefficients when applied to slender cones. The present theory is estimated to be reliable provided that Mb is less than 0.7.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114817325","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}
T N ANY AEROELASTIC ANALYSIS by collocation methods, both structural and aerodynamic influence coefficients must be known. We consider here the derivation of the aerodynamic influence coefficients (AICs) from the simplest of the aerodynamic theories—that of strip theory in which the flow along any section of the wing can be considered as two-dimensional. The type of AICs necessary in an aeroelastic analysis must relate the controlpoint forces, F (rather than pressures) to the deflections, h, or streamwise slopes. In the present treatment, we prefer the deflections rather than streamwise slopes as the generalized coordinates because the deflections have a more general meaning on a cambered surface and deflection influence coefficients are more readily obtained from a structural analysis than slope influence coefficients. Accordingly, we define a steady matrix of AICs, [CHS], by
{"title":"Aerodynamic Influence Coefficients from Strip Theory","authors":"W. Rodden","doi":"10.2514/8.8333","DOIUrl":"https://doi.org/10.2514/8.8333","url":null,"abstract":"T N ANY AEROELASTIC ANALYSIS by collocation methods, both structural and aerodynamic influence coefficients must be known. We consider here the derivation of the aerodynamic influence coefficients (AICs) from the simplest of the aerodynamic theories—that of strip theory in which the flow along any section of the wing can be considered as two-dimensional. The type of AICs necessary in an aeroelastic analysis must relate the controlpoint forces, F (rather than pressures) to the deflections, h, or streamwise slopes. In the present treatment, we prefer the deflections rather than streamwise slopes as the generalized coordinates because the deflections have a more general meaning on a cambered surface and deflection influence coefficients are more readily obtained from a structural analysis than slope influence coefficients. Accordingly, we define a steady matrix of AICs, [CHS], by","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129875432","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":"Parametric Study of the Influence of Propellant Sloshing on the Stability of Spacecraft","authors":"H. Bauer","doi":"10.2514/8.9198","DOIUrl":"https://doi.org/10.2514/8.9198","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128881915","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 Vectorial Representation of Aerodynamic Forces Acting on a Thin Rectangular Wing Oscillating Harmonically in Supersonic Potential Flow","authors":"J. P. Chawla","doi":"10.2514/8.7651","DOIUrl":"https://doi.org/10.2514/8.7651","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"21 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120984638","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":"Publication/Subscription/Member Data","authors":"S. Pivko","doi":"10.2514/8.7709","DOIUrl":"https://doi.org/10.2514/8.7709","url":null,"abstract":"","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"364 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124577203","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}
Abstract : Principle topics discussed are: the work of Carnot and Clausius; enthalpy and free enthalpy - the ideal heat engine; propulsion in the void; entropy in gas flow; entropy in shock waves; structure of shock waves; connections between entropy and molecular theory; chemical equilibrium; nonequilibrium states.
{"title":"The Role of Entropy in the Aerospace Sciences- Daniel and Florence Guggenheim Memorial Lecture","authors":"J. Ackeret","doi":"10.2514/8.8882","DOIUrl":"https://doi.org/10.2514/8.8882","url":null,"abstract":"Abstract : Principle topics discussed are: the work of Carnot and Clausius; enthalpy and free enthalpy - the ideal heat engine; propulsion in the void; entropy in gas flow; entropy in shock waves; structure of shock waves; connections between entropy and molecular theory; chemical equilibrium; nonequilibrium states.","PeriodicalId":336301,"journal":{"name":"Journal of the Aerospace Sciences","volume":"74 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2012-08-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114533252","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：