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2. installed.) Delta II and III launch vehicles- (TDT Tests 510 and 519): In order to extend the viahle market for the Delta II launch vehicle series, a new payload fairing was developed to allow for a larger payload capacity. Two versions of the payload fairing were developed for mission specific operations. referred to as the haseline and stretched configurations. The new fairings wen: uniqm: in that they incorporate a modified Haack nose instead of the classical cone/cylinder construction. The new fairing hoattail was at a much shallower angle than had heen used in the past. According to NASA space vehicle design crileria." 1' the new configurations are considered"stahlc huffet-prone" hodies of revolution. Because of the significant fairing configuration changes. it was decided to experimentally determine the unsteady pressure environment during transonic flight. A test of these Delta II configurations was conducted in the TDT in 1995. Figure 69 is a photograph of the Delta II model sting-mounted in the TDT. The ohjective of the test was to measure the fluctuating pressure distrihution along the fairing configurations to later he used in the development or forcing functions that arc required in the performance of spacecraft/launch vehicle coupled loads analyses.
3. In 1996. a similar test was conducted for a Delta III configuration. A photograph of the Delta mounted model is shown in Fig. 71.
4. Fig. 69- Photograph of the Di.:ltaII launch vehicle model. Baseline Configuration