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tamara a smith

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Rocket enginesComparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m℗ø(350 psia)Tamara A. Smith

Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m℗ø(350 psia)

Tamara A. Smith · National Aeronautics and Space Administration, Scientific and Technical Information Office

Sayfa sayısı yok · 1987

Nozzles / Rockets (Aeronautics) / Rocket engines

Nozzle designComparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m(2) (350 psia)Tamara A. Smith

Comparison of theoretical and experimental thrust performance of a 1030:1 area ratio rocket nozzle at a chamber pressure of 2413 kN/m(2) (350 psia)

Tamara A. Smith · Lewis Research Center

21 sayfa · 1987

Rocket nozzles / Nozzle design

Rockets (Aeronautics)Boundary layer development as a function of chamber pressure in the NASA Lewis 1030:1 area ratio rocket nozzleTamara A. Smith

Boundary layer development as a function of chamber pressure in the NASA Lewis 1030:1 area ratio rocket nozzle

Tamara A. Smith · National Aeronautics and Space Administration

Sayfa sayısı yok · 1988

Nozzles / Rockets (Aeronautics)