Technical Approach to Evaluating the Loss in Rocket Motor Specific Impulse Due to Discontinuity of the Nozzle Block Contour

Author： Solomonov Yu.  

Publisher： Springer Publishing Company

ISSN： 0010-5082

Source： Combustion, Explosion, and Shock Waves, Vol.46, Iss.5, 2010-09, pp. : 593-598

Disclaimer: Any content in publications that violate the sovereignty, the constitution or regulations of the PRC is not accepted or approved by CNPIEC.

Previous Menu Next

Abstract

Related content

Experimental Study of Thrust Performance of a Hybrid Rocket Motor with Various Methods of Oxidizer Injection

By Potapkin A. V.   Lee T.  

Combustion, Explosion, and Shock Waves, Vol. 40, Iss. 4, 2004-07 ,pp. : 386-392

Springer Publishing Company

Access to resources Recommend Favorite

Technical

By  

Focus on Powder Coatings, Vol. 2002, Iss. 1, 2002-01 ,pp. : 2-6

Elsevier

Access to resources Recommend Favorite

Burning of Nano-Aluminized Composite Rocket Propellants

By Luca L.   Galfetti L.   Severini F.   Meda L.   Marra G.   Vorozhtsov A.   Sedoi V.   Babuk V.  

Combustion, Explosion, and Shock Waves, Vol. 41, Iss. 6, 2005-11 ,pp. : 680-692

Springer Publishing Company

Access to resources Recommend Favorite

Scientific, technical

By  

Fuel and Energy Abstracts, Vol. 43, Iss. 5, 2002-09 ,pp. : 325-329

Elsevier

Access to resources Recommend Favorite

Scientific, technical

By  

Fuel and Energy Abstracts, Vol. 44, Iss. 1, 2003-01 ,pp. : 18-19

Elsevier

Access to resources Recommend Favorite