This content is not included in
your SAE MOBILUS subscription, or you are not logged in.
Application of KTRAN Transonic Small Disturbance Code to the Challenger Business Jet Configuration with Winglets
Annotation ability available
Sector:
Language:
English
Abstract
A Transonic Small Disturbance code originally developed at Canadair for the analysis of 3D wing/body/pylon/store configurations (AGARD CP-412-8) has been extended to calculate flows around complete aircraft such as the Challenger Executive Jet.
The program uses a modified Transonic Small Disturbance equation discretized in cartesian and cylindrical coordinates and a grid embedding technique to capture flow details around specific components. The equation is solved using a successive line over-relaxation technique applied in two phases. In the first phase, the flow field is relaxed in the overall crude grid and in the winglet cylindrical grid. In the second phase, the crude grid and the various embedded fine grids are relaxed in alternating steps. The interaction between the various grids is through simple linear interpolation.
The program is capable of representing Challenger-type wide body fuselages, large aspect ratio supercritical wings, high by-pass turbofan engines and canted winglets. Correlations with wind tunnel and flight test data demonstrate the capability of the method.
Recommended Content
Technical Paper | Aerodynamic Design Approach to the Stall/Spin Problem - The VariViggen |
Technical Paper | CaRnard - A New Roadable Aircraft Concept |
Technical Paper | A High Efficiency Fuselage Propeller (”Fusefan”) for Subsonic Aircraft |
Authors
Topic
Citation
Kafyeke, F., Piperni, P., and Robin, S., "Application of KTRAN Transonic Small Disturbance Code to the Challenger Business Jet Configuration with Winglets," SAE Technical Paper 881483, 1988, https://doi.org/10.4271/881483.Also In
References
- Boppe, C.W. Stern, M.A. “Simulated Transonic Flows for Aircraft With Nacelles, Pylons, and Winglets” AIAA-80-0130 January 1980
- Kafyeke, F. “Prediction of Wing-Body-Store Aerodynamics Using a Small Perturbation Method and a Grid Embedding Technique” AGARD CP 412-8 April 1986
- Lomax, H. Bailey, F.R. Balhaus, W.R. “On the Numerical Simulation of the Three Dimensional Transonic Flow with Application to the C-141 Wing” NASA TN D-6933 August 1973
- Rosen, B.S. “Transonic Analysis of Canted Winglets” AIAA-84-0302 January 1984
- Boppe, C.W. “Transonic Flow Field Analysis of Wing Fuselage Configurations” NASA CR 3243 May 180
- Werner, J. “Slender Body Boundary Condition Corrections for Body Shapes Modelled by an Approximate Computational Surface” Grumman Aerodynamics Report 390-77-04 June 1977
- Vachris, A.F. Yaeger L.S. “Quick Geometry - A Rapid Response Method For Modelling Configuration Geometry” NASA SP-390 October 1975 49 73
- Jameson, A. Caughey, D.A. “Numerical Calculation of the Transonic Flow Past a Swept Wing” Courant Institute of Mathematical Sciences Report COO-3077-140 June 1977
- South, J.C. “Comments on Difference Schemes for the Three Dimensional Transonic Small Disturbance Equation for Swept Wings” NASA TM X-71980 July
- Waggoner, E.G. “Computational Transonic Analysis For A Supercritical Transport Wing-Body Configuration” AIAA paper 80-0129 January 1980
- Shankar, V. Malmuth, N.D. “Computational and Simplified Analytical Treatment of Transonic Wing/ Fuselage/Pylon/Store Interactions” AIAA-80-0127 January 1980
- Boppe, C.W. “Aerodynamic Analysis for Aircraft With Nacelles, Pylons, and Winglets at Transonic Speeds” NASA CR 4066 April 1987