Calculation Techniques for Inviscid Two-Dimensional Supersonic Airflow

摘要

Techniques for calculating the change in properties of inviscid supersonic airflow passing over or through various two-dimensional bodies are discussed in this report. Low supersonic (M less than 4) airflows and high supersonic (M greater than 4) airflows are considered separately. Flow phenomena considered include normal shock waves, oblique shock waves, insentropic expansions, and conical shock waves for cones at zero degrees angle of attack. The adjustments required for swept wings are also discussed. Printouts of computer subroutines designed to carry out the described calculation procedures are included in an appendix to the report. Examples describing the use of the calculation techniques and computer subroutines for a swept wing, and for two typical ramjet inlets are included. A final appendix includes charts that can be used as calculation aids for airflows at Mach numbers up to 4. (Author)