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Prof. Dr. Sher Afghan Khan

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  1. Pathan, Khizar Ahmed and Dabeer, Prakash S and Khan, Sher Afghan (2019) Influence of expansion level on base pressure and reattachment length. CFD Letters, 11 (5). pp. 22-36. ISSN 2180-1363
  2. Khan, Sher Afghan and Aabid, Abdul and Mokashi, Imran and Al-Robaian, Abdul Rehman Abdullah and Alsagri, Ali Sulaiman (2019) Optimization of two-dimensional wedge flow field at supersonic Mach number. CFD Letters, 11 (5). pp. 80-97. ISSN 2180-1363
  3. Khan, Sher Afghan and Aabid, Abdul and Ghasi, Fharukh Ahmed Mehaboobali and Al-Robaian, Abdulrahman and Alsagri, Ali Sulaiman (2019) Analysis of area ratio in a CD nozzle with suddenly expanded duct using CFD method. CFD Letters, 11 (5). pp. 61-71. ISSN 2180-1363
  4. Pathan, Khizer Ahmed and Dabeer, Prakash S and Khan, Sher Afghan (2019) Investigation of base pressure variations in internal and external suddenly expanded flows using CFD analysis. CFD Letters, 11 (4). pp. 32-40. ISSN 2180-1363
  5. Siddiqi, Mohammad Umar and Gulhane, P. Nitin and Khan, Sher Afghan and Taler, Jan and Cebula, Arthur and Oclon, Pawel and Patil, Rajesh (2019) Numerical investigation of semiempirical relations representing the local Nusselt number magnitude of a pin fin heat sink. Heat Transfer—Asian Research. pp. 1-32. ISSN 1099-2871 (In Press)
  6. Siddique, Mohd Umair and Khan, Sher Afghan and Al-Robaian, Abdulrahman and Ansari, Eman (2019) Numerical study of heat transfer augmentation using pulse jet impinging on Pin Fin heat sink. CFD letters, 11 (3). pp. 84-91. ISSN 2180-1363
  7. Quadros, Jaimon Dennis and Khan, Sher Afghan and Antony, A J (2018) Study of base pressure behavior in a suddenly expanded duct at supersonic mach number regimes using statistical analysis. Journal of Applied Mathematics and Computational Mechanics, 17 (4). pp. 59-72. ISSN 2299-9965
  8. Khan, Sher Afghan and Aabid, Abdul and Saleel, Ahamad C. (2019) CFD simulation with analytical and theoretical validation of different flow parameters for the wedge at supersonic Mach number. International Journal of Mechanical & Mechatronics Engineering IJMME-IJENS, 19 (1). pp. 170-177. ISSN 2227-2771
  9. Khan, Sher Afghan and Aabid, Abdul and Saleel, Ahmed (2019) Influence of micro jets on the flow development in the enlarged duct at supersonic Mach number. International Journal of Mechanical & Mechatronics Engineering, 19 (1). pp. 70-82. ISSN 2227-2771
  10. Quadros, Jaimon Dennis and Khan, Sher Afghan and Antony, A J (2018) Base pressure behaviour in a suddenly expanded duct at supersonic mach number regimes using Taguchi design of experiments. Mechanics and Mechanical Engineering, 22 (4). pp. 1077-1097. ISSN 1428-1511
  11. Aabid, Abdul and Khan, Ambareen and Mazlan, Nur Musfira and Ismail, Mohd Azmi and Akhtar, M. Nishat and Khan, Sher Afghan (2019) Numerical simulation of suddenly expanded flow at Mach 2.2. International journal of Engineering & Advanced Technology (IJEAT), 8 (3). pp. 457-462. ISSN 2249-8958
  12. Khan, Sher Afghan and Mohiuddin, A K M and Saleel, Ahmad C and G M, Fharukh (2019) Investigation of the effects of nozzle exit mach number and nozzle pressure ratio on axisymmetric flow through suddenly expanded nozzles. International Journal of Engineering and Advanced Technology (IJEAT), 8 (3). pp. 570-578.
  13. Monis, Renita Sharon and Crasta, Asha and Khan, Sher Afghan (2019) An effect of sweep angle on roll damping derivative for a Delta wing with curved leading edges in unsteady flow. International Journal of Mechanical and Production Engineering Research and Development (IJMPERD), 9 (2). pp. 361-373. ISSN 2249-6890
  14. Hamizi, Ilya Bashiera and Khan, Sher Afghan (2019) Aerodynamics investigation of delta wing at low Reynold’s number. CFD letters, 11 (2). pp. 32-41. ISSN 2180-1363
  15. Saleel, Ahmed and Baig, Maughal Ahmed Ali and Khan, Sher Afghan (2018) Experimental investigation of the base flow and base pressure of sudden expansion nozzle. In: International Conference on Aerospace and Mechanical Engineering (AeroMech17), 21st-22nd November 2017, Batu Ferringhi, Penang.
  16. Siddique, Mohd Umair and Gulhane, N P and Al-Robaian, Abdul Rehman A and Khan, Sher Afghan (2019) On numerical investigation of semi-empirical relations representing local nusselt number at lower nozzle-target spacing’s. International Journal of Engineering, 32 (1). pp. 137-145. ISSN 1025-2495
  17. Khan, Sher Afghan and Alrobaian, Abdul Rahman and Asad Ullah, Mohammed and Rao, Ashwin (2019) Threaded spikes for bluff body base flow control. Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 53 (2). pp. 194-203.
  18. Khan, Sher Afghan and Alrobaian, Abdul Rahman and Asad Ullah, Mohammed and Khan, Abdul Mohsin (2019) Grooved cavity as a passive controller behind backward facing step. International Journal of Advanced Research in Fluid Mechanics and Thermal Sciences, 53 (2). pp. 185-193. ISSN 2289-7879
  19. Mohammed Umair, Siddque and Alrobaian, Abdul Rahman and Khan, Sher Afghan and Gnanagonda Kashinath, Marthande and Rajesh, Patil (2018) Numerical investigation of critical range for the occurrence of secondary peaks in the Nusselt distribution curve. CFD Letters, 10 (2). pp. 1-17. ISSN 2180-1363
  20. Al-Robaian, Abdul Rehman A and Khan, Sher Afghan and Asad Ullah, Mohammed and G. M., Fharrukh Ahmed and Imtiyaz, A (2018) A new approach to low-cost open-typed subsonic compressible flow wind tunnel for academic purpose. International Journal of Mechanical and Production Engineering Research and Development (IJMPERD), 8 (6). pp. 383-394. ISSN 2249-6890

Most Viewed Items

Item titleViews
1Experimental investigation of flow through convergent nozzle and the influence of micro jets on the enlarged duct flow field789
2Active control of flow through the nozzles at sonic Mach number770
3Influence of micro jets on wall pressure for area ratio 3.24726
4Studies on wall pressure flow control by micro jets for high area ratio724
5Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges723
6The effect of micro jets on wall pressure for sonic under expanded flow712
7Studies on wall pressure of sonic flow through the converging nozzles for different area ratios682
8Control of suddenly expanded flow at low supersonic Mach numbers642
9Control of base pressure with micro jets for area ratio 2.4610
10Studies on flow from converging nozzle and the effect of nozzle pressure ratio for area ratio of 6.25 599
11Effect of angle of attack on damping derivatives of delta wing with full sine wave curved leading edge591
12Effect of mach number on wall pressure flow field for area ratio 2.56585
13Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56581
14Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow580
15Supersonic similitude for oscillating non-planar wedge570
16An investigation of base flow control by wall pressure analysis in a suddenly expansion nozzle569
17Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges566
18Effect of level of expansion and inertia level in a suddenly expanded flow562
19Studies on flow from convergent nozzle with sudden expansion and control effectiveness under the influence of micro jets 561
20Base pressure studies from over expanded nozzle for area ratio 2.56554
21Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges 552
22Stability derivatives of a delta wing with straight leading edge in the Newtonian limit551
23Stabilty derivatives in the newtonian limit550
24Experimental study of suddenly expanded flow from correctly expanded nozzles546
25Influence of low length-to-diameter ratio and nozzle pressure ratio in an abruptly expanded flow546
26Effect of mach number in a suddenly expanded flow for area ratio 4.84546
27Control of base pressure with micro jets:part-I540
28Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD538
29Active control of base pressure in suddenly expanded flow for area ratio 4.84538
30Combined effect of relief and level of expansion in a suddenly expanded flow537
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