OPTIMIZING CONVERGENT-DIVERGENT ROCKET NOZZLE GEOMETRY (30°/10°) TO ENHANCE THE ALTITUDE PERFORMANCE OF MODEL ROCKETS USING SOLID SUGAR PROPELLANTS

Berdiyev, Usmon

Муҳандислик ва Иқтисодиёт · 2026-yil

Annotatsiya

This paper investigates the thermodynamic and gas-dynamic optimization of de Laval nozzle geometry to maximizethe flight altitude of model rockets using sugar-based solid propellants. Standard nozzle configurations may experience internalflow separation and divergence losses. To address this issue, a specific convergent-divergent profile featuring a 30° inletangle and a 10° exit angle was designed and experimentally evaluated. Flight tests were conducted using a standardized 700 grocket body loaded with a 400 g KNSU/KNSB propellant grain modified with an eco-friendly, waste-derived tobacco ash catalystrich in K₂CO₃ and CaCO₃. While the baseline nozzle configurations consistently achieved peak altitudes of 200 m, the optimized30°/10° nozzle configuration reached an apogee of 300 m, representing a 50% increase in performance. The findingssuggest that optimizing the exit divergence angle may reduce expansion losses and improve the effective axial exhaust velocity

Maqola ma’lumotlari
MualliflarBerdiyev, Usmon
JurnalМуҳандислик ва Иқтисодиёт
Nashr sanasi2026-07-01
Jild4
Son7
Betlar176-180
TilIngliz

Maqolaning asl sahifasi

Kalit so‘zlar

rocket nozzle, de Laval geometry, convergence angle, exit angle, solid propellant, KNSU, flight performance, altitude optimization.

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