Engineering Aerothermal Analysis for X-34 Thermal Protection System Design
- 1 March 1999
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Spacecraft and Rockets
- Vol. 36 (2) , 216-228
- https://doi.org/10.2514/2.3452
Abstract
No abstract availableKeywords
This publication has 22 references indexed in Scilit:
- Aeroheating Predictions for X-34 Using an Inviscid Boundary-Layer MethodJournal of Spacecraft and Rockets, 1999
- Heating Analysis of the Nosecap and Leading Edges of the X-34 VehicleJournal of Spacecraft and Rockets, 1999
- Thermostructural Analysis of X-34 Wing Leading-Edge Tile Thermal Protection SystemJournal of Spacecraft and Rockets, 1999
- Global Aeroheating Wind-Tunnel Measurements Using Improved Two-Color Phosphor Thermography MethodJournal of Spacecraft and Rockets, 1999
- Computational/experimental aeroheating predictions for X-33 Phase II vehiclePublished by American Institute of Aeronautics and Astronautics (AIAA) ,1998
- Approximate method for calculating heating rates on three-dimensional vehiclesJournal of Spacecraft and Rockets, 1994
- Aerodynamic heating environment definition/thermal protection systemselection for the HL-20Journal of Spacecraft and Rockets, 1993
- Flowfield and vehicle parameter influence on results of engineering aerothermal methodsJournal of Spacecraft and Rockets, 1991
- Application of axisymmetric analog for calculating heating in three-dimensional flowsJournal of Spacecraft and Rockets, 1987
- Engineering flowfield method with angle-of-attack applicationsJournal of Spacecraft and Rockets, 1985