Hyper-X Mach 10 engine flowpath development - Fifth entry test conditions and methodology

Author:

Bakos R.1,Tsai C.-Y.1,Rogers R.2,Shih A.2

Affiliation:

1. GASL, Inc., Ronkonkoma, NY

2. NASA, Langley Research Center, Hampton, VA

Publisher

American Institute of Aeronautics and Astronautics

Reference21 articles.

1. 1964 NO

2. Aboundary layer trip (BLT) strip was designed for the nominal conditions of the AR225 nozzle with expected boundary layer transition occurring at a station 8-9 inches downstream. A photo of the HSM with the flat FB is shown in Figure 4. TEST HARDWARE INSTALLATION

3. Surface Data: Instrumentation layout on the body and cowl side surfaces of the HSM includes 184 pressure and heat flux instrument ports. PCB pressure transducers are used and are recess mounted behind .063-inch diameter,06-inch deep orifices. The platinum thin-film heat flux gages areflush mounted. Optical Diagnostics: As indicated in Figure 5, the HSM has two sets of windows on each side to permit optical access to the isolatorcombustor and internal nozzle sections of the flowpath. The schlieren system uses a highpower LED as the light source, and four monochrome CCD cameras to capture sequential images of the flow field during a test run.1111For the images acquired in these tests, the LED pulse width was 4 jis and the cameras were set at a shutter speed 1/16000 (62 us). In addition to providing a two-dimensional view of the test flow, the four-frame sequential schlieren (4FSS) images provide information about flow establishment and termination due to driver gas arrival.

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