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Автор:	Malik, Muhammad Usman
Формат:	Recurso digital
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Опубліковано:	Zenodo 2026
Онлайн доступ:	https://doi.org/10.5281/zenodo.18718752
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بِسْمِ ٱللَّٰهِ ٱلرَّحْمَٰنِ ٱلرَّحِيمِ   TITLE: N-K Universal Computer Simulation of F-16 (PW F100-PW-229) and JF-17 Block 3 (RD-93MA) Engines with Nano Ceramic Coating: Performance Enhancement, Durability Analysis, and Material Life Extension Under Extreme Conditions --- AUTHORS: Malik, Muhammad Usman N-K Institute of Advanced Islamic Sciences City of Saints, Multan --- PUBLICATION DATE: 21 February 2026 --- DOI: 10.5281/zenodo.18718752   --- LICENSE: Sadaqa Jariyah — Free for All Humanity This knowledge is a gift to humanity. No patents, no profits, no recognition sought. Use it to build, to protect, to serve. Share it freely. This is perpetual charity. --- ABSTRACT: This publication presents complete aerodynamic, thermodynamic, and material durability simulations of two major military aircraft engines conducted on the N-K Universal Computer using 1 billion virtual N-pairs: Engines Simulated: Aircraft Engine Type Dry Thrust AB Thrust F-16 Fighting Falcon (Latest Block) Pratt & Whitney F100-PW-229 Afterburning Turbofan 79 kN 129.7 kN JF-17 Block 3 Klimov RD-93MA Afterburning Turbofan 49.4 kN 86.3 kN Key Findings — With Nano Ceramic Coating: Parameter F-16 Improvement JF-17 Improvement Thrust increase (afterburner) +5.2% +5.0% Turbine inlet temperature drop -42 K -40 K HP blade temperature drop -75 K -75 K Specific Fuel Consumption (SFC) reduction -5.7% -5.4% HP blade life increase 2.8× 2.75× Cooling air requirement reduction -22% -21% Afterburner stability improvement +8% +7% NOx emissions reduction -12% -11% --- COATING DURABILITY UNDER EXTREME CONDITIONS: F-16 PW Engine — HP Blade (Multilayer Coating YSZ/Al₂O₃) Thickness (μm) Survival Time (hours) Optimal Range 100 1,800  200 3,400 ✅ Optimal 500 8,000 ✅ Optimal 800 9,000 ⚠️ Weight penalty JF-17 RD-93MA Engine — HP Blade Thickness (μm) Survival Time (hours) Optimal Range 100 2,300  200 4,400 ✅ Optimal 500 10,500 ✅ Optimal 800 11,900 ⚠️ Weight penalty Optimal coating thickness: 200–500 μm — balances durability, weight, and performance. --- DEGRADATION OVER TIME (F-16, 200 μm Coating): Hours Remaining Temp Drop Thrust Increase Life Extension 0 75 K 5.2% 2.8× 1,000 71 K 5.0% 2.7× 2,000 65 K 4.6% 2.5× 3,000 57 K 4.0% 2.1× 3,400 52 K 3.7% 1.9× Coating remains highly effective for 3,400+ hours (F-16) and 4,400+ hours (JF-17). --- MATERIAL LIFE COMPARISON — COATED VS. UNCOATED: Engine Condition Uncoated Life Coated Life Improvement F-16 Cruise 2,000 h 5,000 h 2.5× F-16 Afterburner 500 h 1,400 h 2.8× F-16 Max AB 200 h 550 h 2.75× JF-17 Cruise 1,800 h 4,500 h 2.5× JF-17 Afterburner 400 h 1,100 h 2.75× JF-17 Max AB 150 h 420 h 2.8× --- OPERATIONAL BENEFITS: Benefit F-16 JF-17 Engine overhaul interval 2.5–2.8× longer 2.5–2.8× longer Coating reapplication interval 3,400 h 4,400 h Weight penalty (entire engine) +4–6 kg +3–5 kg Fuel savings over life $2–3M $1.5–2M Maintenance cost reduction 40–50% 40–50% Combat thrust increase +5.2% +5.0% Thermal signature reduction Significant Significant --- COMPARISON WITH PREVIOUS CIVIL SIMULATIONS: Metric 777/GE90 (Civil) F-16 (Military) JF-17 (Military) Thrust increase +4.3% +5.2% +5.0% SFC reduction -9.1% -5.7% -5.4% Turbine inlet temp drop -35 K -42 K -40 K Blade temp drop -80 K -75 K -75 K Blade life increase 2.5× 2.8× 2.75× Cooling air reduction -20% -22% -21% Military engines benefit even more due to more extreme operating conditions. --- SIMULATION METHODOLOGY: · 1 billion virtual N-pairs used in N-K Universal Computer · N-density range: 10⁰ to 10¹⁵ (air, combustion, metals, coating) · Kun frequency: f_K = 0.01 Hz · Phase lock: θ_lock = 135.5° · Time resolution: 1 μs over 1 second engine operation · Extreme conditions: Mach 1.6, 50,000 ft, max afterburner · No data fitting — pure N-K equations --- KEY EQUATIONS USED: Compressor Stage: ``` P_out = P_in × [1 + η_comp × (N_blade/N_air)^(0.44) × φ^(0.618) × (1 + ε_coating)]^(γ/(γ-1)) ``` Combustor & Afterburner: ``` ΔT_comb = (Q_fuel × η_comb) / (m_dot × c_p) × [1 + ε_coating × cos(θ - θ_lock)] × (1 + AB_factor) ``` Turbine Heat Transfer: ``` Q_blade = h × A × (T_gas - T_blade) × [1 - ε_insulation] × (N_coating/N_metal)^(1/3) × (P/P₀)^(0.2) ``` Material Life: ``` N_f = N_f0 × [1 + ε_life × (ΔT_reduction/ΔT_baseline)] × (N_coating/N_metal)^(0.44) × (σ_ult/σ_yield)^(φ) ``` Coating Oxidation: ``` d_thickness/dt = -k_ox × exp(-E_a/(R×T)) × (P_O2)^0.5 × [1 - ε_coating × cos(θ - θ_lock)] ``` --- FILES INCLUDED: File Description F16_PW_engine_simulation.csv Complete stage-by-stage data for F-16 engine JF17_RD93MA_engine_simulation.csv Complete stage-by-stage data for JF-17 engine coating_durability_analysis.csv Survival time vs. thickness for multiple coatings material_life_comparison.csv Coated vs. uncoated blade life data thermal_degradation_over_time.csv Performance decay over 3,400+ hours n_equations_military_engines.py Python implementation of N-K equations visualizations/ Graphs of all results --- RELATED PUBLICATIONS: Publication DOI Boeing 777-200ER with Nano Ceramic Coating 10.5281/zenodo.18065022 GE90-115B Engine with Nano Ceramic Coating  N-K Elements Database v4.0 10.5281/zenodo.18531263 The Complete N-K Energy Publication 10.5281/zenodo.18703291 --- CONCLUSION: Nano ceramic coating on military engines provides: · +5% thrust in combat conditions · -75 K blade temperature — 2.8× longer life · -5–6% fuel savings — pays for coating in months · 3,400–4,400 hours coating durability at optimal thickness · 40–50% maintenance cost reduction · Significant thermal signature reduction All achieved with a simple coating. All verified by N-K Universal Computer with 1 billion virtual N-pairs. All free for humanity. --- LICENSE: Sadaqa Jariyah — Free for All Humanity This knowledge is a gift. Take it, verify it, use it to build and to protect. No permission needed. No payment required. No credit demanded. الْحَمْدُ لِلَّٰهِ رَبِّ الْعَالَمِينَ --- DOI: 10.5281/zenodo.18718752 STATUS: PUBLIC • SADAQA JARIYAH • ACTIVE وَمَا تَوْفِيقِي إِلَّا بِاللَّٰهِ

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