Aeronautics & Astronautics - Fluid Sciences > Aerodynamics: Page 14

No. 26126 General nonlifting body of 3-D source panel distribution No. 26127 Sphere's drag coefficient vs Reynolds number No. 26130 Nonadiabatic flow No. 26131 Adiabatic flow diagram No. 26132 Nonisentropic flow No. 26133 Isentropic flow diagram No. 26134 Flow through oblique shock wave No. 26135 Flow through normal shock wave No. 26141 Isentropic flow over an airfoil No. 26143 Properties of shock wave as a function of Mach number No. 26144 Subsonic-combustion ramjet engine No. 26145 Sketch of Pitot tube for subsonic flow No. 26146 Pitot tube in supersonic flow No. 26149 Turbulence propagated from body in subsonic flow No. 26150 Turbulence propagated from body in supersonic flow No. 26154 Chapter 9 road map No. 26155 Geometry for an oblique shock No. 26158 Attached shock angle of corner flow No. 26159 Attached shock on a wedge No. 26160 Detached shock on a wedge No. 26161 Attached shock in corner flow No. 26162 Detached shock in corner flow No. 26163 Weak and strong shocks No. 26170 Normal shock inlet No. 26171 Oblique shock inlet No. 26174 Attached shock on a wedge No. 26175 Solid boundary shock wave reflection No. 26176 Mach reflection No. 26177 Right- and left-running shock waves intersection No. 26178 Intersection of two shock waves running left No. 26179 Isentropic compression corner No. 26180 Shock compression corner No. 26181 Flat plate at an angle of attack in supersonic flow No. 26184 Quasi-one-dimensional flow finite control volume No. 26188 Supersonic nozzle No. 26189 Supersonic diffuser No. 26191 Sound breaking isentropic flow through a convergent-divergent nozzle No. 26192 Mach distribution across a nozzle No. 26193 Nozzle wise pressure ratio No. 26194 Sound breaking isentropic flow through a convergent-divergent nozzle No. 26195 Nonsound breaking isentropic flow through convergent-divergent nozzle No. 26196 Mach number for isentropic subsonic nozzle flow No. 26197 Pressure ration for isentropic subsonic nozzle flow No. 26198 Choked flow showing mass flow vs exit pressure No. 26199 Supersonic nozzle flow diagram with shock inside No. 26200 Mach along supersonic nozzle with normal shock inside No. 26201 Pressure ratio along nozzle for nozzle flow with a shock inside No. 26202 Supersonic nozzle flow with normal shock at exit No. 26203 Mach number along supersonic nozzle with shock at exit No. 26204 Pressure ratio along supersonic nozzle with shock at exit
 

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