NASA Technical Reports Server (NTRS) 19890016586: Influence Of Thickness And Camber On The Aeroelastic Stability Of Supersonic Throughflow Fans: An Engineering Approach - Info and Reading Options
By NASA Technical Reports Server (NTRS)
"NASA Technical Reports Server (NTRS) 19890016586: Influence Of Thickness And Camber On The Aeroelastic Stability Of Supersonic Throughflow Fans: An Engineering Approach" and the language of the book is English.
“NASA Technical Reports Server (NTRS) 19890016586: Influence Of Thickness And Camber On The Aeroelastic Stability Of Supersonic Throughflow Fans: An Engineering Approach” Metadata:
- Title: ➤ NASA Technical Reports Server (NTRS) 19890016586: Influence Of Thickness And Camber On The Aeroelastic Stability Of Supersonic Throughflow Fans: An Engineering Approach
- Author: ➤ NASA Technical Reports Server (NTRS)
- Language: English
Edition Identifiers:
- Internet Archive ID: NASA_NTRS_Archive_19890016586
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"NASA Technical Reports Server (NTRS) 19890016586: Influence Of Thickness And Camber On The Aeroelastic Stability Of Supersonic Throughflow Fans: An Engineering Approach" Description:
The Internet Archive:
An engineering approach was used to include the nonlinear effects of thickness and camber in an analytical aeroelastic analysis of cascades in supersonic acial flow (supersonic leading-edge locus). A hybrid code using Lighthill's nonlinear piston theory and Lanes's linear potential theory was developed to include these nonlinear effects. Lighthill's theory was used to calculate the unsteady pressures on the noninterference surface regions of the airfoils in cascade. Lane's theory was used to calculate the unsteady pressures on the remaining interference surface regions. Two airfoil profiles was investigated (a supersonic throughflow fan design and a NACA 66-206 airfoil with a sharp leading edge). Results show that compared with predictions of Lane's potential theory for flat plates, the inclusion of thickness (with or without camber) may increase or decrease the aeroelastic stability, depending on the airfoil geometry and operating conditions. When thickness effects are included in the aeroelastic analysis, inclusion of camber will influence the predicted stability in proportion to the magnitude of the added camber. The critical interblade phase angle, depending on the airfoil profile and operating conditions, may also be influenced by thickness and camber. Compared with predictions of Lane's linear potential theory, the inclusion of thickness and camber decreased the aerodynamic stifness and increased the aerodynamic damping at Mach 2 and 2.95 for a cascade of supersonic throughflow fan airfoils oscillating 180 degrees out of phase at a reduced frequency of 0.1.
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