OPTIMIZING CONVERGENT-DIVERGENT ROCKET NOZZLE GEOMETRY (30°/10°) TO ENHANCE THE ALTITUDE PERFORMANCE OF MODEL ROCKETS USING SOLID SUGAR PROPELLANTS
##plugins.pubIds.doi.readerDisplayName##:
https://doi.org/10.5281/zenodo.21629550##article.subject##:
rocket nozzle, de Laval geometry, convergence angle, exit angle, solid propellant, KNSU, flight performance, altitude optimization.##article.abstract##
This paper investigates the thermodynamic and gas-dynamic optimization of de Laval nozzle geometry to maximize
the flight altitude of model rockets using sugar-based solid propellants. Standard nozzle configurations may experience internal
flow separation and divergence losses. To address this issue, a specific convergent-divergent profile featuring a 30° inlet
angle and a 10° exit angle was designed and experimentally evaluated. Flight tests were conducted using a standardized 700 g
rocket body loaded with a 400 g KNSU/KNSB propellant grain modified with an eco-friendly, waste-derived tobacco ash catalyst
rich in K₂CO₃ and CaCO₃. While the baseline nozzle configurations consistently achieved peak altitudes of 200 m, the optimized
30°/10° nozzle configuration reached an apogee of 300 m, representing a 50% increase in performance. The findings
suggest that optimizing the exit divergence angle may reduce expansion losses and improve the effective axial exhaust velocity
Библиографические ссылки
Sutton, G. P. Rocket Propulsion Elements / G. P. Sutton, O. Biblarz. — 9th ed. — Hoboken, NJ : John Wiley & Sons, 2016. — 800
p. — ISBN 978-1-118-75391-0.
Marchi, C. H. Cold-crafted KNSu mechanically pressed burning rate for combustion pressure ranging from 0.9 to 7.7 bar /
C. H. Marchi, A. C. Foltran, D. F. Moro [et al.] // Combustion Science and Technology. — 2023. — Vol. 195, No. 9. — P. 2210–
— DOI: 10.1080/00102202.2021.2011862.
Östlund, J. Supersonic flow separation with application to rocket engine nozzles / J. Östlund, B. Muhammad-Klingmann //
Applied Mechanics Reviews. — 2005. — Vol. 58, No. 3. — P. 143–177. — DOI: 10.1115/1.1894402.
Zebbiche, T. Stagnation temperature effect on the supersonic axisymmetric minimum-length nozzle design with application
for air / T. Zebbiche // Advances in Space Research. — 2011. — Vol. 48, No. 10. — P. 1656–1675. — DOI: 10.1016/j.
asr.2011.08.012.
Anderson, J. D. Modern Compressible Flow: With Historical Perspective / J. D. Anderson. — 4th ed. — New York : McGraw Hill
Education, 2021. — 778 p. — ISBN 978-1-260-47144-1.
Bharti, M. K. Catalytic potential of microsized additives in enhancing the linear burn rate of potassium nitrate–sucrose-based
composite solid propellant strands / M. K. Bharti, L. Bansal, S. Chalia // International Journal of Energetic Materials and
Chemical Propulsion. — 2021. — Vol. 20, No. 4. — P. 61–77. — DOI: 10.1615/IntJEnergeticMaterialsChemProp.2021038209.
Ravanbod, M. Catalytic effect of Fe₂O₃, Mn₂O₃, and TiO₂ nanoparticles on the thermal decomposition of potassium nitrate /
M. Ravanbod, H. R. Pouretedal // Journal of Thermal Analysis and Calorimetry. — 2016. — Vol. 124. — P. 1091–1098. — DOI:
1007/s10973-015-5167-y.
Buragohain, A. Mineralogical characterization of tobacco stalk ash / A. Buragohain, V. Vartic, R. Lalmuanpuii [et al.] //
Environmental Science and Pollution Research. — 2026. — Vol. 33. — P. 10777–10794. — DOI: 10.1007/s11356-026-
-z.
Tashxodjayev, A. M. Qattiq yoqilg‘ili energetik tizimlarning termik tahlili va yonish kinetikasi / A. M. Tashxodjayev, K. S.
Ismoilov // O‘zbekiston Kimyo Jurnali. — 2020. — № 3. — B. 42–49.
Rustamov, K. S. Aerodynamic design and performance analysis of small-scale educational rockets / K. S. Rustamov, A. A.
Tursunov // Technical Science and Innovation. — 2021. — No. 3. — P. 85–92.
Загрузки
##submissions.published##
##issue.issue##
##section.section##
Лицензия
Copyright (c) 2026 MUHANDISLIK VA IQTISODIYOT
Это произведение доступно по лицензии Creative Commons «Attribution» («Атрибуция») 4.0 Всемирная.