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    Effect of advanced rotorcraft airfoil sections on the hover performance of a small-scale rotor model (1988)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A hover test was conducted on a small scale rotor model for two sets of tapered rotor blades. The baseline rotor blade set used a NACA 0012 airfoil section, whereas the second rotor blade set had advanced rotorcraft airfoils distributed along the radius. The experiment was conducted for a range of thrust coefficients and tip speeds, and the data were compared to the predictions of three analytical methods. The data show the advantage of the advanced airfoils at the higher rotor thrust levels; two of the analyses predicted the correct data trends.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2832 , L-16407 , NAS 1.60:2832 , AVSCOM-TP-88-B-001
    Format: application/pdf
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