Accession Number : AD0620013

Title :   ANALYSIS OF FLOW SEPARATION EFFECTS ON THE DYNAMICS OF A LARGE SPACE BOOSTER.

Descriptive Note : Revised ed.,

Corporate Author : LOCKHEED MISSILES AND SPACE CO SUNNYVALE CALIF

Personal Author(s) : Ericsson,Lars-Eric ; Reding,J. Peter

Report Date : 16 NOV 1964

Pagination or Media Count : 10

Abstract : The next generation of manned space boosters, the Saturn-Apollo family, presents the structural dynamicist with the unique situation of having to analyze the response of vehicles that are to a great extent submerged in separated flow. The problem is further aggravated by the occurrence of maximum dynamic pressure in the transonic and low-supersonic speed ranges wherein flow separations completely dominate the aerodynamics. Quasi-steady aerodynamic techniques are used to ascertain the effects that the various types of flow separation have on the aerodynamic damping of the Saturn I-Apollo launch vehicle. A single degree-of-freedom analysis of each of the three lowest bending modes is presented. The analysis uses as an input a lumped-force representation of the experimentally obtained static load distribution. The resulting aerodynamic damping distribution can be related directly to the static-load distribution, and the designer can trace any adverse damping effects back to the static-load distribution and thus to the vehicle geometry. The net aerodynamic damping for part or all of the vehicle, obtained by integration of the damping distribution, agrees well, in general, with available experimental results. (Author)

Descriptors :   (*LAUNCH VEHICLES, AERODYNAMIC CHARACTERISTICS), (*GAS FLOW, SEPARATION), TRANSONIC FLOW, SUPERSONIC FLOW, AERODYNAMIC LOADING, DAMPING, DISTRIBUTION

Distribution Statement : APPROVED FOR PUBLIC RELEASE