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References

1. General (delta wings)

1. Hummel, D.: Experimentelle Untersuchung der Strömung auf der Saugseite eines schlanken Deltaflügels. Z. Flugwiss. 13 (1965), 247 - 252.
2. Visbal, M. R.: Computed unsteady structure of spiral vortex breakdown on delta wings. AIAA Paper 96-2074 (1996).
3. Müller, J. and Hummel, D.: Numerical analysis of the unsteady flow above a slender delta wing at large angles of attack. ICAS Proceedings 2000, Paper ICA0252 (2000).

2. VFE-1 results

1. Drougge, G.: The international vortex flow experiment for computer code validation. ICAS-Proceedings Jerusalem 1988, Vol. 1, pp. XXXV-XLI.
2. Elsenaar, A.; Hjelmberg, L.; Bütefisch, K.-A. and Bannink, W.J.: The international vortex flow experiment. AGARD-CP 437 (1988), Vol.1, pp .9-1 to 9-23.
3. Wagner, B.; Hitzel, S.; Schmatz, M.A.; Schwarz, W.; Hilgenstock, A. and Scherr, S.: Status of CFD validation on the vortex flow experiment. AGARD-CP 437 (1988), Vol. 1, pp. 10-1 to 10-10.
4. Hoeijmakers, H.W.M.: Modelling and numerical simulation of vortex flow in aerodynamics. AGARD-CP 494 (1991), pp. 1-1 to 1-46.

3. VFE-2 results

1. Chu,J. and Luckring, J. M.: Experimental surface pressure data obtained on 65° delta wing across Reynolds number and Mach number ranges. NASA TM 4645 (1996).
2. Luckring, J. M.: Reynolds number and leading-edge bluntness effects on a 65° delta wing. AIAA Paper 2002-0419, 2002.
3. Luckring, J. M.: Transonic Reynolds number and leading-edge bluntness effects on a 65° delta wing. AIAA Paper 2003-0753, 2003.
4. Hummel, D. and Redeker, G.: A new vortex flow experiment for computer code validation. RTO AVT Symposium on “Vortex Flow and High Angle of Attack Aerodynamics”, Loen, Norway, 7-11 May 2001, Meeting Proceedings RTO-MP-069 (I), SYA 8-1 to 8-31 (2003).
5. Pirzadeh, S. Z.: Vortical flow prediction using an adaptive unstructured grid method. RTO AVT Symposium on “Vortex Flow and High Angle of Attack Aerodynamics”, Loen, Norway, 7-11 May 2001, Meeting Proceedings RTO-MP-069 (I), SYA 13-1 to 13-36 (2003).
6. Luckring, J. M.: Compressibility and leading-edge bluntness effects for a 65° delta wing. AIAA Paper 2004-0765, 2004.
7. Luckring, J. M.: Reynolds number, compressibility, and leading-edge bluntness effects on delta-wing aerodynamics. ICAS Proceedings Yokohama 2004, Paper 4.1.4.
8. Hummel, D.: Effects of boundary layer formation on the vortical flow above slender delta wings. RTO AVT Symposium on "Enhancement of NATO Military Flight Vehicle Performance by Management of Interacting Boundary Layer Transition and Separation", Prague, Czech Republic, 4-8 Oct 2004, Meeting Proceedings RTO-MP-AVT-111, 30-1 to 30-22, 2004.
9. Hummel, D.: The second international vortex flow experiment (VFE-2): Objectives and first results. 2nd International Symposium on "Integrating CFD and Experiments in Aerodynamics". .5 - 6 September 2005, Cranfield University, UK. J. Aerospace Engineering, Vol. 220 (2006), Nr. 6: 559 - 568.
10. Klein, C.; Sachs, W.; Henne, U.; Wiedemann, A. and Konrath, R.: Development of PSP technique for application on the VFE-2 65° delta wing configuration in sub- and transonic flow. AIAA Paper 2006-0059 (2006).
11. Konrath, R.; Klein, C.; Engler, R. H. and Otter, D.: Analysis of PSP results obtained for the VFE-2 65° delta wing configuration at subsonic and transonic speed. AIAA Paper 2006-0060 (2006).
12. Schröder, A.; Agocs, J.; Frahnert, H.; Otter, D.; Mattner, H.; Kompenhans, J. and Konrath, R.: Application of Stereo-PIV to the VFE-2 65° delta wing configuration at sub- and transonic speeds. AIAA Paper 2006-3486 (2006).
13. Konrath, R.; Schröder, A. and Kompenhans, J.: Analysis of PIV results obtained for the VFE-2 65° delta wing configuration at sub- and transonic speeds. AIAA Paper 2006-3003 (2006).
14. Konrath, R.; Klein, Ch.; Schroeder, A. and Kompenhans, J.: Combined application of Pressure Sensitive Paint and Particle Image Velocimetry to the flow above a delta wing. 12th International Symposium on Flow Visualization, Sept. 10 - 14, 2006, DLR Goettingen, Germany.
15. Sheplak, M.: The year in review: Aerodynamic measurement technology. Aerospace America, December 2006: 22.
16. Furman, A. and Breitsamter, Ch.: Delta wing steady pressure investigations for sharp and rounded leading edges. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), Vol. 92 (2006), 77 -84.
17. Furman, A. and Breitsamter, Ch.: Investigation of flow phenomena on generic delta wing. ICAS Proceedings 2006.
18. Schiavetta, L. A.; Boelens, O. J. and Fritz, W.: Analysis of transonic flow on a slender delta wing using CFD. AIAA Paper 2006-3171 (2006).
19. Crippa, S. and Rizzi, A.: Numerical investigation of Reynolds number effects on a blunt leading-edge delta wing. AIAA Paper 2006-3001 (2006).
20. Crippa, S. and Rizzi, A.: Initial steady/unsteady CFD analysis of vortex flow over the VFE-2 delta wing. ICAS Proceedings 2006.
21. Furman, A. and Breitsamter, Ch.: Stereo-PIV and Hot-wire investigations on delta wing. Council of European Aerospace Societies (CEAS), 1st European Air and Space Conference, Berlin, 10 - 13 Sep 2007.
22. Crippa, S., Rizzi, A.: Reynolds number effects on blunt leading edge delta wings. Council of European Aerospace Societies (CEAS), 1st European Air and Space Conference, Berlin, 10 - 13 Sep 2007.
23. Schiavetta, L.: Evaluation of URANS and DES predictions of vortical flows over delta wings. PhD thesis, Faculty of Engineering, Department of Aeronautical Engineering, University of Glasgow, 2007.
24. Schiavetta, L. A., Badcock, K. and Cummings, R.: Comparison of DES and URANS for unsteady vortical flows over delta wings. AIAA Paper 2007-1085 (2007).
25. Schiavetta, L. A., Boelens, O. J., Fritz, W. and Cummings, R. M.: Sting effects on transonic delta wing experiments. 3rd International Symposium on Integrating CFD and Experiments in Aerodynamics, 20 - 21 June 2007, US Air Force Academy, CO, USA.
26. Hummel, D.: The Second International Vortex Flow Experiment (VFE-2): Objectives and present status. AIAA Paper 2007-4446 (2007).
27. Hummel, D.: Review of the Second International Vortex Flow Experiment (VFE-2). AIAA Paper 2008-0377, 2008.
28. Luckring, J. M.: Initial experiments and analysis of vortex flow on blunt edged delta wings. AIAA Paper 2008-0378, 2008.
29. Konrath, R., Klein, Ch. and Schroeder, A.: PSP and PIV investigations on the VFE-2 configuration in sub- and transonic flow. AIAA Paper 2008-0379, 2008.
30. LeRoy, J. F., Rodriguez, O. and Kurun, S.: Experimental and CFD contribution to delta wing vortical flow understanding. AIAA Paper 2008-0380, 2008.
31. Furman, A. and Breitsamter, Ch.: Turbulent and unsteady flow characteristics of delta wing vortex systems. AIAA Paper 2008-0381, 2008.
32. Coton, F., Mat, S. and Galbraith, R.: Low speed wind tunnel characterization of the VFE-2 wing. AIAA Paper 2008-0382, 2008.
33. Luckring, J. M. and Hummel, D.: What was learned from the new VFE-2 experiments? AIAA Paper 2008-0383, 2008.
34. Nangia, R. K.: Semi-empirical prediction of vortex onset and progression on 65° delta wings (RTO-AVT-113, VFE-2 facet). AIAA Paper 2008-0384, 2008.
35. Fritz, W.: Numerical simulation of the peculiar subsonic flow-field about the VFE-2 delta wing with rounded leading edge. AIAA Paper 2008-0393, 2008.
36. Gürdamar, E., Ortakaya, Y., Kaya, S. and Korkem, B.: Some factors influencing the vortical flow structures on delta wings. AIAA Paper 2008-0394, 2008.
37. Schiavetta, L. A., Boelens, O. J., Crippa, S., Cummings, R. M., Fritz, W. and Badcock, K. J.: Shock effects on delta wing vortex breakdown. AIAA Paper 2008-0395, 2008.
38. Cummings, R. M. and Schütte, A.: Detached-eddy simulation of the vortical flowfield about the VFE-2 delta wing. AIAA Paper 2008-0396, 2008.
39. Crippa, S. and Rizzi, A.: Steady, subsonic CFD analysis of the VFE-2 configuration and comparison to wind tunnel data. AIAA Paper 2008-0397, 2008.
40. Schütte, A. and Lüdeke, H.: Numerical investigations on the VFE 2 65-degree rounded leading edge delta wing using the unstructured DLR-TAU-Code. AIAA Paper 2008-0398, 2008.
41. Fritz, W. and Cummings, R. M.: What was learned from the numerical simulations for the VFE-2? AIAA Paper 2008-0399, 2008. 
42. AVT-113 Final Report: Details for citation will be given after the publication of the document.