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Prof. Dr. Sher Afghan Khan

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  1. Mohd Umair, Siddique and Ansari, Emad and Khan, Sher Afghan and Alrobaian, Abdulrahman (2019) On numerical investigation of semi-empirical relation representing development length for a fluid flow in a closed conduit. CFD Letters, 11 (6). pp. 63-71.
  2. Renita, Sharon Monis and Crasta, Asha and Khan, Sher Afghan (2019) Evaluation of stiffness derivative for a delta wing with straight leading edges in unsteady flow. International Journal of Engineering and Advanced Technology (IJEAT), 8 (3S). pp. 754-762. ISSN 2249 – 8958
  3. Khan, Sher Afghan and Asadullah, Mohammad and G.M, Fharukh Ahmed. and Jalaluddeen, Ahmed and Baig, Maughal Ahmed Ali (2018) Flow control with aerospike behind bluff body. International Journal of Mechanical and Production Engineering Research and Development (IJMPERD), 8 (3). pp. 1001-1008. ISSN 2249-6890
  4. Pathan, Khizer Ahmed and Dabeer, Prakash S and Khan, Sher Afghan (2019) Effect of nozzle pressure ratio and control jets location to control base pressure in suddenly expanded flows. Journal of Applied Fluid Mechanics, 12 (4). pp. 1127-1135. ISSN 1735-3572
  5. Asadullah, Mohammed and Khan, Sher Afghan and Soudagar, Manzoore Elahi M and T. R., Vaishak (2019) A comparison of the effect of single and multiple cavities on base flows. In: 5th IEEE International Conference on Engineering Technologies and Applied Sciences (ICETAS) 2018, 22nd-23rd Nov. 2018, Bangkok, Thailand.
  6. S, Parashurama and Saleel, C. Ahmed and M. S., Govindegowda and Khan, Sher Afghan (2019) Hydrocarbons as alternative refrigerants in domestic refrigerators. International Journal of Innovative Technology and Exploring Engineering (IJITEE), 8 (6S3). pp. 496-501. ISSN 2278-3075
  7. Warimani, Mohammadsalman and Azami, Muhammad Hanafi and Khan, Sher Afghan (2019) Challenges and solutions for using liquid fuels in aviation industry. International Journal of Engineering and Advanced Technology (IJEAT), 8 (2s2). pp. 288-290. ISSN 2249–8958
  8. 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
  9. 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
  10. 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
  11. 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
  12. 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)
  13. 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
  14. 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
  15. 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
  16. 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
  17. 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
  18. 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
  19. Khan, Sher Afghan and Mohiuddin, 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.
  20. 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

Most Viewed Items

Item titleViews
1Experimental investigation of flow through convergent nozzle and the influence of micro jets on the enlarged duct flow field812
2Active control of flow through the nozzles at sonic Mach number787
3Influence of micro jets on wall pressure for area ratio 3.24747
4Effect of aspect ratio with angle of attack of an oscillating hypersonic delta wing with straight leading edges744
5Studies on wall pressure flow control by micro jets for high area ratio742
6The effect of micro jets on wall pressure for sonic under expanded flow729
7Studies on wall pressure of sonic flow through the converging nozzles for different area ratios707
8Control of suddenly expanded flow at low supersonic Mach numbers658
9Control of base pressure with micro jets for area ratio 2.4628
10Studies on flow from converging nozzle and the effect of nozzle pressure ratio for area ratio of 6.25 617
11Effect of angle of attack on damping derivatives of delta wing with full sine wave curved leading edge609
12Effect of mach number on wall pressure flow field for area ratio 2.56605
13Combined effect of nozzle pressure ratio and screech prone supersonic mach number in a suddenly expanded flow602
14Control of suddenly expanded flows from correctly expanded and under expanded nozzles at supersonic mach number for area ratio 2.56598
15An investigation of base flow control by wall pressure analysis in a suddenly expansion nozzle592
16Supersonic similitude for oscillating non-planar wedge588
17Effect of level of expansion and inertia level in a suddenly expanded flow585
18Estimation of stability derivatives of an oscillating hypersonic delta wings with curved leading edges585
19Studies on flow from convergent nozzle with sudden expansion and control effectiveness under the influence of micro jets 579
20Base pressure studies from over expanded nozzle for area ratio 2.56574
21Stability derivatives of a delta wing with straight leading edge in the Newtonian limit572
22Stabilty derivatives in the newtonian limit572
23Effect of angle of attack on stiffness derivative of an oscillating supersonic delta wing with curved leading edges 570
24Effect of mach number in a suddenly expanded flow for area ratio 4.84565
25Experimental study of suddenly expanded flow from correctly expanded nozzles564
26Influence of low length-to-diameter ratio and nozzle pressure ratio in an abruptly expanded flow562
27Effect of mach number on stiffness and damping derivatives for oscillating hyersonic non-planar wedge556
28Control of base pressure with micro jets:part-I556
29Experimental and numerical studies on flow from axisymmetric nozzle flow with sudden expansion for Mach 3.0 using CFD555
30Active control of base pressure in suddenly expanded flow for area ratio 4.84554
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