[1] Anderson JD (1989) Hypersonic and high temperature gas dynamics. 2nd edn. 978-964-2751-04-4, New York: 25-346.
[2] Benjamine J, Garland A, Swanson G (1957) Aerodynamic heating and boundary-layer transition on a 1/10-power nose shape in free flight at mach numbers up to 6.7. NASA Research Memorandum Bressette Langley Aeronautical Laboratory NASA: 5-17.
[3] Chauvin L, Katherine C(1957) Boundary-layer transition and heat-transfer measurements from flight tests of blunt and sharp cones at mach numbers from 1.7 to 4.7. NASA RM L57DO4: 12-27.
[4] Howard S, Walter E (1957) Heat-Transfer and pressure distribution on six blunt noses at a mach number of 2. NASA Research Memorandum Bressette Langley Aeronautical Laboratory NASA: 21-28.
[5] Kumar A(1980) Laminar and turbulent flow solutions with radiation and ablation injection for jovian entry. AIAA J 90(5): 80-88.
[6] Sutton K (1985) Air radiation revisited in thermal design of aeroassisted orbital transfer vehicles. AIAA J 96(12): 419-441.
[7] رحمانپور م، ابراهیمی ر، شمس م (1385) حل میدان با احتساب واکنشهای شیمیایی غیرتعادلی به منظور محاسبه چگالی الکترونی اطراف یک جسم با دماغه پخ. دهمین کنفرانس دینامیک شاره‌ها، یزد، دانشگاه یزد، دانشکده مهندسی مکانیک.
[8] Gollan RJ (2011) Numerical modeling of radiating superorbital flows. 3th edn. The University of Queensland Brisbane 4072, Australia: 29-37.
[9] Potter, DF (2011) Modelling of radiating shock layers for atmospheric entry at Earth and Mars. Scientaa AC Abore, s4029188 phD Thesis: 48-82.
[10] کریمیان ر، غفاریان م، عزیزی ح (1392) حل جریان ماورا صوت روی بدنه موشک با در نظر گرفتن اثرات هوای دما بالا جهت تعیین گرمایش آیرودینامیکی. طرح پژوهشی دانشگاه صنعتی امیرکبیر، دانشکده مهندسی هوا و فضا.
[11] Benjamin S, Roy H, Paul HS, Baumanb T , Oliver TA (2014) Modeling hypersonic entry with the fully-implicit Navier–Stokes (FIN-S) stabilized finite element flow solver. Comput Fluids 92(4): 281-292.
[12] Ekert ER (1986) Engineering relations for heat transfer and friction in high-velocity laminar and turbolent boundral-layer flow over surfaces with constant pressure and temperature. Trans ASME 78(6): 127-131.
[13] Zein TF (1999) Heat transfer in the melt layer of a simple ablation model. J Thermophys Heat Tr 13(4): 58-72.
[14] Miner EW (1975) Computer user’s guide for a chemically reacting viscous shock layer code, NASA CR-2551: 5-29.
[15] Bryknia G, Scott S (1998) An approximate axisymmetric viscous shock layer aeroheating method for three-dimensional bodies. AIAA NASA/TM198-207890: 4-17.
[16] Chen YK, Milos FS (2012) Finite-rate ablation boundary conditions for carbon-phenolic heat-shield. NASA Ames Research Center, Moffett Field, CA 94035-1000: 8-34.
[17] Park C (2002) Calculation of stagnation point heat transfer for pioneer venus probes. Proposed NASA Technical Memorandum: 12-26.
[18] هولمن ج، تاجور ح‌ح (1989) انتقال حرارت. چاپ پنجم. کانون کتاب دانشگاهی، مرکز خدمات فرهنگی سالکان: 240-354.
[19] Anderson JD (1967) Nongray Radiative transfer effects on the radiating stagnation region shock layer and stagnation point heat transfer. NOLTR U.S. Naval Ordnance Laboratory, White Oak MD: 67-104.
)