Rocket or Satellite Launch Vehicle's (SLV) Nose Cone Shape's Aerodynamic Drag Coefficients in Various Mach Numbers (Subsonic - Transonic - Supersonic) - PART 1
- Citation Author(s):
- Submitted by:
- Sambit Supriya Dash
- Last updated:
- Sat, 03/04/2023 - 11:41
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The rocket nose-cone shapes have been generated by blending few conic sections together (two conic sections in one) and the simulated against mach number regime from subsonic through transonic to supersonic. The aerodynamic drag coefficients have been recoded for each shape for each mach number.
Since ages, aerodynamic drag and heating in re-entering, planetary landing and launching has been a point of major concern. Thus far, witnessing through studies and practicality shown the evolution of usages from hemispherical series, ellipse, hack and ogive series for space launch vehicle nose design. This research work comprises of study of aerodynamic and heat flux parameters intensively in subsonic, transonic and supersonic regimes that’s along a journey of a SLV. Crux of the article highlights its novelty through proper design in CAD software CATIA V5 and computational comparative analysis with the aid of ANSYS platform on Fluent method, of various unique nose cone shapes such as (i) blended shape nose cones (blending and tapering the combination of parabolic concave, parabolic convex, elliptic and hemispherical) and (ii) spiked nose cones, with variation in individual sizes. The basis of performance quantification has been taken in terms of aerodynamic parameters and heat conduction parameters for SLV’s nose cone shape along the varying speed range of the vehicle. The qualitative relations and results would facilitate in prototyping possible design to provide the control/balance of both aerodynamic drag coefficient for SLV. In case of required fast orbital launching the shape of cone should be penetrating the shock barrier to gain an increase rate of momentum, in contrast the landing case requires the drag as alliance and a much blunt cone would be used. In any operating condition, the heat transfer to the surface of vehicle shouldn’t be significant, through the aspect of nose shape analysis optimum proportion of both parameters would be upraised. This study would mostly useful for in-operation convertible nosecones in future via technological advancements(e.g shape memory alloy, mechanical sensors) for enhancing efficiency and increasing safety of vehicle, crew/astronauts/systems from heating by adapting the shape required for varying surrounding conditions.
Please, read the MachNumbers.txt, params.txt and shapeNames.txt from the readme.zip to understand what exactly the dataset records and range of attributes represent. Also look at the picture WT.png format to see the meaning of T and WT as extensions in the record names in the dataset.
readme.zip password (if any): 1001
- Extract the .zip file to get the DATASET in .xlsx file ALL_CD_M_PART_1.zip (11.80 kB)
- Schematic of the Nose Cone (Labeling) WT.png (134.47 kB)
- Extract to get the files describing the terms aforementioned in the instruction section. readme.zip (1.46 kB)