AERODİNAMİK ISINMA KESTİRİM ARACININ DOĞRULANMASI

Year 2020, Volume: 40 Issue: 1, 53 - 63, 30.04.2020

Buğra Şimşek Sıtkı Uslu Mehmet Ak

Abstract

Yüksek hızlı hava araçlarının gövde sıcaklıklarını ve aerodinamik ısı akılarını hesaplama yazılımı olan, bir boyutlu aerodinamik ısınma ve ısıl aşınma kestirim yazılımı, AeroheataBS’in doğrulama çalışmaları yürütülmüştür. Şok denklemleri, düz plaka üzeri taşınım ısı transferi yaklaşımları, Eckert’in referans sıcaklık yöntemi ve değiştirilmiş Newton yasası aerodinamik ısınmanın hesaplanmasında kullanılmıştır. Denklemler açık olarak ayrıklaştırılmış ve sayısal olarak çözülmüştür. Işınım ile olan ısı transferi de dikkate alınmıştır. Uçuş hızı, uçuş irtifası ve hücum açısı zamana bağlı olarak tanımlanmıştır. Hesaplamaların doğruluğu literatürde bulunan uçuş verileriyle ve hesaplamalı akışkanlar dinamiği çalışmalarının sonuçlarıyla kıyaslanarak değerlendirilmiştir. Kıyaslamalarda gözlemlenen uyumlu sonuçlar AeroheataBS yazılımında kullanılan yöntemin aerodinamik ısınmanın ve gövde sıcaklıklarının kestiriminde kullanılabileceğini göstermiştir.

Keywords

Aerodinamik ısınma, füzelerin ısıl tasarımı, ısıl koruma sistemleri

VALIDATION OF AERODYNAMIC HEATING PREDICTION TOOL

Abstract

Validation of one-dimensional aerodynamic heating and ablation prediction program, AeroheataBS to calculate transient skin temperatures and heat fluxes for high-speed vehicles has been performed. In the tool shock relations, flat plate convective heating expressions, Eckert’s reference temperature method and modified Newtonian flow theory are utilized to compute local heat transfer coefficients. Corresponding governing equations are discretized explicitly and numerically solved. Time varying flight conditions including velocity, altitude and angle of attack serve as input to the program. In order to examine the accuracy of aerodynamic heating capabilities of AeroheataBS, calculated temperature histories are compared with flight data of the X-15 research vehicle, a modified von-Karman nose shaped body, cone-cylinder-flare configuration and results of conjugate computational fluid dynamics studies. Comparative studies show that computed values are in good agreement with the reference data and prove that methodology established in AeroheataBS is appropriate for estimating aerodynamic heating and structural thermal response.

Keywords

Aerodynamic heating, thermal design of missiles, thermal protection systems

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