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Computational Results for the Effects of External Disturbances on Transition Location on Bodies of Revolution from Subsonic to Supersonic Speeds and Comparisons with Experimental Data
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Abstract
Computational experiments have been performed for a few configurations in order to investigate the effects of external flow disturbances on the extent of laminar flow and wake drag. Theoretical results have been compared with experimental data for the AEDC cone, for Mach numbers from subsonic to supersonic, and for both free flight and wind tunnel environments. The comparisons have been found to be very satisfactory, thus establishing the utility of the present method for the design and development of “laminar flow” configurations and for the assessment of wind tunnel data. In addition, the present paper presents results of calculations concerning the effects of unit Reynolds numbers on transition. This phenomenon has been observed by a few experimental investigators but has been analyzed in detail for the first time in the present paper with the aid of the theoretical predictions. In addition to the AEDC cone, computations have been performed for an ogive body of revolution at zero angle of attack and supersonic Mach numbers. Results are presented for transition Reynolds number and wake drag for external disturbances corresponding to free air and the test section of the AEDC-VKF tunnel. These results have been found to compare quite well with wind tunnel data for cases when surface suction is applied as well as when suction is absent. Finally, the theoretical results reveal some interesting trends for transition Reynolds number for the ogive body under both free air and tunnel conditions.
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Goradia, S., Bobbitt, P., and Harvey, W., "Computational Results for the Effects of External Disturbances on Transition Location on Bodies of Revolution from Subsonic to Supersonic Speeds and Comparisons with Experimental Data," SAE Technical Paper 892381, 1989, https://doi.org/10.4271/892381.Also In
References
- Dougherty, N. S. Influence of Wind Tunnel Noise on the Location of Boundary-Layer Transition on a Slender Cone at Mach Number from 0.2 to 5.5. AEDC TR-78-44 March 1980
- Fisher, D. F. Dougherty, N. S. Flight and Wind-Tunnel Correlation of Boundary Layer Transition on AEDC Transition Cone AGARD CP-339 February 1983
- Dougherty, N. S. Fisher, D. F. Boundary Layer Transition on a 10-Degree Cone AIAA Paper No. 80-0154 1980
- Harvey, W. D. Bobbitt, P. J. Some Anomalies Between Wind Tunnel and Flight Transition Results AIAA 14th Fluids and Plasma Dynamics Conference Palo Alto, CA June 23-25 1981
- Goradia, S. H. Bobbitt, P. J. Theoretical Investigation for the Effects of Sweep, Leding Edge Geometry and Spanwise Pressure Gradients on Transition and Wave Drag at Transonic Correlation SAE Paper 881484 October 3-4 1988
- Goradia, S. H. Bobbitt, P. J. Morgan, H. L. Ferris, J. C. Harvey, W. D. Results of Correlations for Transition Location on a Clean-up Glove Installed on an F-14 Aircraft and Design Studies for a Laminar Glove for the X-29 Aircraft Accounting for Spanwise Pressure Gradient Proceedings of a Symposium NASA Langley Research Center II April 19-21 1988
- Goradia, S. H. Bobbitt, P. J. Ferris, J. C. Harvey, W. D. Theoretical Investigations and Correlative Studies for NLF, HLFC, and LFC Swept Wings at Subsonic, Transonic, and Supersonic Speeds SAE Paper 871861 October 5-8 1987
- Goradia, S. H. Morgan, H. L. A New, Improved Method for Separating Turbulent Boundary Layer for Aerodynamic Performance Prediction of Trailing Edge Stall Air-foils AIAA 4th Applied Aerodynamics Conference San Diego, CA June 9-11 1986
- Goradia, Suresh H. Morgan, Harry L. Theoretical Methods and Design Studies for NLF and HLFC Swept Wings at Subsonic and Transonic Speeds Natural Laminar Flow and Laminar Flow Control Symposium 2 Hampton, VA March 16-19 1987
- Goradia, S. H. Lyman, V. L. Laminar Stall Prediction and Estimation of C LMax Journal of Aircraft 11 9 September 1974 528 536
- Goradia, S. H. The Method of Characteristics Perturbation Technique as Applied to Airfoil Design Lockheed-Georgia Company March 1968
- Stevens, W. A. Goradia, S. H. Braden, J. A. Mathematical Model for Two-Dimensional Multi-Component Airfoils in Viscous Flow, NASA CR 1843
- Goradia, S. H. Mehta, J. M. A Method for Three-Dimensional Boundary Layer Flow Computation by Integral Techniques Lockheed-Georgia Engineering Report LG77ER0095 July 1977
- Pate, S. R. Investigations of Drag Reduction by Boundary Layer Suction on a Body of Revolution at Mach Numbers 2.5, 3.0, and 3.5 AEDC-TR-65-36 February 1965