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Spacecraft Boost and Entry Heat Transfer
- Aerospace Standard
- AIR1168/11A
- Stabilized
Downloadable datasets available
Annotation ability available
Sector:
Issuing Committee:
Language:
English
Scope
The prediction of vehicle temperatures during ascent through the earth’s atmosphere requires an accurate knowledge of the aerodynamic heating rates occurring at the vehicle surface. Flight parameters required in heating calculations include the local airstream velocity, pressure, and temperature at the boundary layer edge for the vehicle location in question. In addition, thermodynamic and transport air properties are required at these conditions.
Both laminar and turbulent boundary layers occur during the boost trajectory. Experience has shown that laminar and turbulent heating are of equivalent importance. Laminar heating predominates in importance in the stagnation areas, but the large afterbody surfaces are most strongly affected by turbulent heating. Once the local flow conditions and corresponding air properties have been obtained, the convective heating rate may be calculated for a particular wall temperature. This assumes that the boundary layer flow regime (that is, turbulent, laminar, or transitory) has also been established, so that a heating theory corresponding to the particular flow conditions may be selected.
This section presents theoretical methods for computing boost vehicle surface aerodynamic heating rates. First, procedures are given for computing the local flow distributions around the vehicle. Second, methods are given for computing the convective heating rates, using the flow parameters found previously.
Rationale
This document has been determined to contain basic and stable technology which is not dynamic in nature
Data Sets - Support Documents
| Title | Description | Download |
|---|---|---|
| Unnamed Dataset 1 | ||
| TABLE 1 | Values of Constants | |
| TABLE 2 | Thermal Properties of Materials | |
| TABLE 3 | Reference Atmospheric Constants | |
| TABLE 4 | Atomic Collisions Per Mode | |
| TABLE 5 | Pressure Ratios ( ) | |
| TABLE 6 | Pressure Ratios | |
| TABLE 7 | Chord Parameters ( ) | |
| TABLE 8 | Afterbody Pressures ( ) | |
| TABLE 9 | u /u = f (h, M sin θ ) | |
| TABLE 10 | Summary of Maximum Values of C /C | |
| TABLE 11 | Resume of Laminar and Turbulent Heating Equations for Lifting Entry | |
| TABLE 12 | Surface Temperatures | |
| TABLE 13 | Surface Temperatures |
Issuing Committee
AC-9 Aircraft Environmental Systems Committee
Furthers the advancement of technology related to the research, design, test and utilization of aircraft environmental and anti-icing/deicing systems. Develops and updates standards, recommended practices, and information reports contributing to the quality, economy, and safety of commercial and military aircraft.
Reference
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