Reynolds and Mach number simulation of Apollo and Gemini re-entry and comparison with flight
Year: 1968
Type: article
Abstract: A comprehensive investigation in the AE-VKF wind tunnels was conducted on the Apollo 011 and Gemini 3 spacecraft configurations in order to resolve several anomalies between preflight predictions and flight data.Attention was focused on simulating the actual Apollo Command Module (011) and Gemini spacecraft (GT3) 'as flown" in model construction over a Mach number range of 3 to 20.The investigation indicated that the influence of the ablator (heat shield) geometry of the Apollo Command Module causes a significant change in trim angle of attack and resulting decrease in available lift-to-drag ratio.In addition, a very strong viscous influence exists in the initial portion of re-entry for both the Apollo and Gemini spacecrafts.Also, the Mach number influence extends up to about Mach 14 which is substantially higher than previous blunt body investigations have indicated.Comparisons of the AEDC wind tunnel data with existing flight data are made and generally excellent agreement exists.
Authors: B. J. GRIFFITH, D. E. Boylan
Language: English
Subfield: Applied Mathematics
Field: Mathematics
Domain: Physical Sciences
Open Access status: green
OpenAlex ID: W2758219383