UH-60A External Stores Support System Fixed Provision Fairings Drag Determination

Williams, Robert; MacMullin, Robert; Miess, Joseph O.; Buckanin, Robert M.; Abbott, William Y

doi:10.21236/ada147188

1984

DOI: 10.21236/ada147188

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UH-60A External Stores Support System Fixed Provision Fairings Drag Determination

Robert Williams¹,

Robert MacMullin²,

Joseph O. Miess³

et al.

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2004

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“…This testing has included hover and forward flight performance tests conducted by the U.S. Army Aviation Engineering Flight Activity (AEFA) at Edwards AFB (Refs. [2][3][4][5][6] and tests of a highly-instrumented rotor at the U.S. Army Aeroflightdynamics Directorate and NASA Ames Research Center (Refs. [7][8][9][10][11][12][13][14][15][16].…”

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confidence: 99%

Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel

Shinoda¹,

Yeo²,

Norman³

2004

j am helicopter soc

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ABTRACTA full-scale four-bladed UH-60 rotor system was tested in the NASA Ames 80-by 120-Foot Wind Tunnel. A quality data set at low forward speed, 0 to 80 knots, has been obtained to support future rotor developments and analysis improvements. To evaluate the NASA Ames 80-by 120-Foot Wind Tunnel as a hover testing facility, rotor performance data were compared with predictions, UH-60 aircraft flight test data, and UH-60 model-scale data from other test facilities. Results indicate that valid hover data for this size rotor can be obtained from this facility at low to medium thrust conditions. Comparisons with flight test and model-scale data demonstrate the variability between existing data sets. Predictions show good agreement with full-scale data. To evaluate the analytical modeling in the 0 to 80 knot speed range, forward flight rotor performance data were acquired and compared with predictions. Comparisons were also made with existing model-scale and flight test data. Power calculations show fair to good agreement with full-scale wind tunnel data at advance ratios between 0.10 to 0.19 and poor agreement at advance ratios below 0.10. Comparisons with flight test and model-scale data show good agreement at all advance ratios tested. Propulsive force calculations show good correlation with full-scale wind tunnel data at advance ratios of 0.10 to 0.19. Report Documentation PageForm Public reporting burden for the collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to a penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. DESCRIPTION OF THE TESTThe following section provides a brief description of the test, including the model, the primary measurement system and the test conditions. A more detailed description of the test and the facility can be found in Ref. 23. ModelThe experiment was conducted in the NASA Ames 80-by 120-Foot Wind Tunnel using a production Sikorsky Aircraft UH-60A rotor system mounted on NASA's Large Rotor Test Apparatus (LRTA). Figure 1 shows the model installed in the wind tunnel.The rotor system, including the hub, spindles, blades, and swashplate, is identical to the one used on the production aircraft. The rotor is four-bladed with coincident flap and lag articulation provided at the blade root by elastomeric bearings. The elastomeric bearing, through the rotor spindle, also allows blade pitch motion. No bifilars were ...

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mentioning

confidence: 99%

Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel

Shinoda¹,

Yeo²,

Norman³

2004

j am helicopter soc

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UH-60A External Stores Support System Fixed Provision Fairings Drag Determination

Cited by 1 publication

References 0 publications

Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel

Rotor Performance of a UH-60 Rotor System in the NASA Ames 80- by 120-Foot Wind Tunnel

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