THEORETICAL AND EXPERIMENTAL STUDY OF SCALING METHOD IN THE ROTOR BLADE ICE ACCRETION TEST

Open Access
Author:
Han, Yiqiang
Graduate Program:
Aerospace Engineering
Degree:
Master of Science
Document Type:
Master Thesis
Date of Defense:
None
Committee Members:
  • Jose Palacios, Thesis Advisor
  • Edward C Smith, Thesis Advisor
Keywords:
  • Helicopter Icing
  • Scaling Method
  • Ice Accretion Test
Abstract:
In the ice accretion test, due to the limitation of test section size and icing condition capability of the test facility, an icing test on the full sized airfoil is not applicable; therefore, to find a properly scaled airfoil which can reproduce essentially the same non-dimensional ice shape is of great interest. Because of the special structure and operating environment, the helicopter is more prone to be affected by the icing phenomena during flight. To study these icing features, the Adverse Environment Rotor Test Stand Lab (AERTS) from V/STOL Research Center of Excellence has built a brand new state-of-art rotor blade icing test facility. In this article, the calibration procedure of the test facility is firstly introduced. Calibration experiments for both standard 1 inch diameter cylinder rotor and 10.5 inch chord NACA 0012 rotor blade are presented. 26 cylinder tests and 37 airfoil tests were conducted to explore the facility capability of reproducing icing conditions and correct ice shape. A calibrated data base of 10 nozzle configurations for the full range of the facility is obtained. The scheme of scaling method is then proposed and guided the 4 of scaling tests. Test results are compared with both literature and AERTS own database. The ice shapes presented in this article all correlate well with references.