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Simulations of the Mars Helicopter Test Propeller in Hover Configuration at Martian Pressure and Air DensityIn order to properly validate experimental data, a theoretical model must be generated and converge with the results. Providing possible results for future testing can help experimenters better understand the results they are getting. Certain effects cannot be shown during experimentation, and must therefore be quantified through another means. The Mars Helicopter is currently being tested in the N242 wind tunnel at NASA Ames Research Center, which can reach a density and pressure similar to Mars. A test propeller was analyzed in a computational fluid dynamics solver. The propeller blades were previously modeled, and were simulated in the full experimental setup, which includes the blast shields, rotor stand and tunnel walls, to thoroughly generate the effects of the true testing conditions. Simulations were run using both an isolated hover condition and with the full setup, and results for thrust and total power were quantified. The data generated was used to quantify the impact of the facility on the propeller. These calculations will ultimately be used to help separate these effects from the actual thrust the propeller will generate, this making the data more accurate.
Document ID
20190001241
Acquisition Source
Ames Research Center
Document Type
Contractor Report (CR)
Authors
Wagner, Lauren N.
(Science and Technology Corp. Moffett Field, CA, United States)
Date Acquired
March 6, 2019
Publication Date
February 1, 2019
Subject Category
Computer Operations And Hardware
Aerodynamics
Report/Patent Number
NASA/CR-2019?220062
ARC-E-DAA-TN64363
Funding Number(s)
CONTRACT_GRANT: NNA16BD60C
Distribution Limits
Public
Copyright
Public Use Permitted.
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