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Record Details

Record 56 of 6378
Two-Dimensional Scramjet Inlet Unstart Model: Wind-Tunnel Blockage and Actuation Systems Test
Offline Availability: Go to Request Form
External Online Source: http://www.youtube.com/watch?v=DiVYkFzmPbQ
Author and Affiliation:
Holland, Scott D.(NASA Langley Research Center, Hampton, VA, United States)
Abstract: This supplement to NASA TM 109152 shows the Schlieren video (10 min. 52 sec., color, Beta and VHS) of the external flow field and a portion of the internal flow field of a two-dimensional scramjet inlet model in the NASA Langley 20-Inch Mach 6 Tunnel. The intent of the overall test program is to study (both experimentally and computationally) the dynamics of the inlet unstart; this (phase I) effort examines potential wind-tunnel blockage issues related to model sizing and the adequacy of the actuation systems in accomplishing the start and unstart. The model is equipped with both a moveable cowl and aft plug. Windows in the inlet sidewalls allow limited optical access to the internal shock structure. In the video, flow is from right to left, and the inlet is oriented inverted with respect to flight, i.e., with the cowl on top. The plug motion is obvious because the plug is visible in the aft window. The cowl motion, however, is not as obvious because the cowl is hidden from view by the inlet sidewall. The end of the cowl actuator arm, however, becomes visible above the inlet sidewalls between the windows when the cowl is up (see figure 1b of the primary document). The model is injected into the tunnel and observed though several actuation sequences with two plug configurations over a range of unit freestream Reynolds number at a nominal freestream Mach number of 6. The framing rate and shutter speed of the camera were too slow to fully capture the dynamics of the unstart but did prove sufficient to identify inlet start and unstart. This series of tests indicated that the model was appropriately sized for this facility and identified operability limits required first to allow the inlet to start and second to force the unstart.
Publication Date: Nov 01, 1994
Document ID:
19950009484
(Acquired Dec 28, 1995)
Accession Number: 95N15899
Subject Category: FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number: NASA-TM-109984, NONP-NASA-SUPPL-VT-94-32020
Document Type: Motion Picture
Publisher Information: United States
Contract/Grant/Task Num: RTOP 763-23-35-08
Financial Sponsor: NASA; United States
Organization Source: NASA Langley Research Center; Hampton, VA, United States
Description: In English; DVD contains .mov file; sound; color; 10 min., 53 sec.
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: No Copyright
NASA Terms: ENGINE INLETS; FLOW DISTRIBUTION; FLOW VISUALIZATION; FREE FLOW; HYPERSONIC INLETS; HYPERSONIC WIND TUNNELS; INLET FLOW; SCHLIEREN PHOTOGRAPHY; SUPERSONIC COMBUSTION RAMJET ENGINES; WIND TUNNEL TESTS; ACTUATORS; BLOCKING; PLUGS; SHOCK WAVE INTERACTION; TWO DIMENSIONAL MODELS
Miscellaneous Notes: Videotape Supplement; Videotape supplement: 10 min. 52 sec. playing time, in color, in VHS and Beta formats
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