Abstract
A rotor blade operating above the 'delocalization' tip Mach number produces a large-amplitude, high-frequency, impulsive noise. A dominant feature of the flow field created by such a rotor blade is the radiating shock wave which extends off the blade tip and propagates to the far field. Predicting the acoustic signature of this rotor requires a detailed knowledge of the flow properties (velocity, density, pressure) in the vicinity of the radiated shock wave both on the blade itself and in the near field. Current numerical techniques tend to smear the shock wave, particularly the portions off the blade surface, resulting in an inaccurate flow field description. The paper describes a method of applying a shock-fitting algorithm to a three-dimensional, full potential rotor code. This approach maintains the flow physics by directly invoking conservation laws as internal boundary conditions at the shock surface. Results show that the shock discontinuity is maintained using the shock-fitting technique. Comparisons with other methods show improvement in the characterization of the shock as a discontinuity.
| Original language | English (US) |
|---|---|
| Title of host publication | Annual Forum Proceedings - American Helicopter Society |
| Publisher | Publ by American Helicopter Soc |
| Pages | 379-386 |
| Number of pages | 8 |
| Volume | 1 |
| State | Published - May 1990 |
| Event | 46th Annual Forum Proceedings of the American Helicopter Society. Part 1 (of 2) - Washington, DC, USA Duration: May 21 1990 → May 23 1990 |
Other
| Other | 46th Annual Forum Proceedings of the American Helicopter Society. Part 1 (of 2) |
|---|---|
| City | Washington, DC, USA |
| Period | 5/21/90 → 5/23/90 |
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ASJC Scopus subject areas
- Aerospace Engineering
- Transportation
Cite this
Three-dimensional shock fitting for transonic rotor acoustics. / Vincent, Thomas E.; Wells, Valana; Rutherford, John W.
Annual Forum Proceedings - American Helicopter Society. Vol. 1 Publ by American Helicopter Soc, 1990. p. 379-386.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Three-dimensional shock fitting for transonic rotor acoustics
AU - Vincent, Thomas E.
AU - Wells, Valana
AU - Rutherford, John W.
PY - 1990/5
Y1 - 1990/5
N2 - A rotor blade operating above the 'delocalization' tip Mach number produces a large-amplitude, high-frequency, impulsive noise. A dominant feature of the flow field created by such a rotor blade is the radiating shock wave which extends off the blade tip and propagates to the far field. Predicting the acoustic signature of this rotor requires a detailed knowledge of the flow properties (velocity, density, pressure) in the vicinity of the radiated shock wave both on the blade itself and in the near field. Current numerical techniques tend to smear the shock wave, particularly the portions off the blade surface, resulting in an inaccurate flow field description. The paper describes a method of applying a shock-fitting algorithm to a three-dimensional, full potential rotor code. This approach maintains the flow physics by directly invoking conservation laws as internal boundary conditions at the shock surface. Results show that the shock discontinuity is maintained using the shock-fitting technique. Comparisons with other methods show improvement in the characterization of the shock as a discontinuity.
AB - A rotor blade operating above the 'delocalization' tip Mach number produces a large-amplitude, high-frequency, impulsive noise. A dominant feature of the flow field created by such a rotor blade is the radiating shock wave which extends off the blade tip and propagates to the far field. Predicting the acoustic signature of this rotor requires a detailed knowledge of the flow properties (velocity, density, pressure) in the vicinity of the radiated shock wave both on the blade itself and in the near field. Current numerical techniques tend to smear the shock wave, particularly the portions off the blade surface, resulting in an inaccurate flow field description. The paper describes a method of applying a shock-fitting algorithm to a three-dimensional, full potential rotor code. This approach maintains the flow physics by directly invoking conservation laws as internal boundary conditions at the shock surface. Results show that the shock discontinuity is maintained using the shock-fitting technique. Comparisons with other methods show improvement in the characterization of the shock as a discontinuity.
UR - http://www.scopus.com/inward/record.url?scp=0025432260&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=0025432260&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:0025432260
VL - 1
SP - 379
EP - 386
BT - Annual Forum Proceedings - American Helicopter Society
PB - Publ by American Helicopter Soc
ER -