SHAMITHA, A. (2020). Computation of stability derivative for a wing for specific heat ratio= 1.66 for hypersonic flow. TJPRC Pvt. Ltd.
シカゴスタイル引用形SHAMITHA, A. Computation of Stability Derivative for a Wing for Specific Heat Ratio= 1.66 for Hypersonic Flow. TJPRC Pvt. Ltd, 2020.
MLA引用形式SHAMITHA, A. Computation of Stability Derivative for a Wing for Specific Heat Ratio= 1.66 for Hypersonic Flow. TJPRC Pvt. Ltd, 2020.
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