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Solution of Shock with Variable Specific Heat and its Application in Hypersonic Inlet

  • Qin Lisen,
Published/Copyright: March 1, 2000
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International Journal of Turbo and Jet Engines
From the journal International Journal of Turbo and Jet Engines Volume 17 Issue 1

Published Online: 2000-03

©2011 by Walter de Gruyter GmbH & Co.

Articles in the same Issue

  1. CONTENTS
  2. Failure Mode of Thermal Barrier Coatings for Gas Turbine Vanes Under Bending
  3. Aeroacoustic Characteristics of Notched Circular-Slot Jets
  4. Aeroacoustic Characteristics of Notched 2:1 Elliptic-Slot Jets
  5. Solution of Shock with Variable Specific Heat and its Application in Hypersonic Inlet
  6. Review: Recent Investigations on Tip Clearance Flows in Centrifugal Compressors
  7. Calculation of Swirling Recirculating Turbulent Flow Using a Two-Layer Approach
https://doi.org/10.1515/TJJ.2000.17.1.57

Articles in the same Issue

  1. CONTENTS
  2. Failure Mode of Thermal Barrier Coatings for Gas Turbine Vanes Under Bending
  3. Aeroacoustic Characteristics of Notched Circular-Slot Jets
  4. Aeroacoustic Characteristics of Notched 2:1 Elliptic-Slot Jets
  5. Solution of Shock with Variable Specific Heat and its Application in Hypersonic Inlet
  6. Review: Recent Investigations on Tip Clearance Flows in Centrifugal Compressors
  7. Calculation of Swirling Recirculating Turbulent Flow Using a Two-Layer Approach
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