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翻訳と辞書　辞書検索 [ 開発暫定版 ] スポンサード リンク Normal shock tables ： ウィキペディア英語版 Normal shock tables In aerodynamics, the normal shock tables are a series of tabulated data listing the various properties before and after the occurrence of a normal shock wave. With a given upstream Mach number, the post-shock Mach number can be calculated along with the pressure, density, temperature, and stagnation pressure ratios. Such tables are useful since the equations used to calculate the properties after a normal shock are cumbersome. The tables below have been calculated using a heat capacity ratio, $\backslash gamma$, equal to 1.4. The upstream Mach number, $M\_1$, begins at 1 and ends at 5. Although the tables could be extended over any range of Mach numbers, stopping at Mach 5 is typical since assuming $\backslash gamma$ to be 1.4 over the entire Mach number range leads to errors over 10% beyond Mach 5. ==Normal shock table equations== Given an upstream Mach number, $M\_1$, and the ratio of specific heats, $\backslash gamma$, the post normal shock Mach number, $M\_2$, can be calculated using the equation below. $M\_2\; =\; \backslash sqrt\}$ The next equation shows the relationship between the post normal shock pressure, $p\_2$, and the upstream ambient pressure, $p\_1$. $\backslash frac\; =\; \backslash frac\; -\; \backslash frac$ The relationship between the post normal shock density, $\backslash rho\_2$, and the upstream ambient density, $\backslash rho\_1$ is shown next in the tables. $\backslash frac\; =\; \backslash frac$ Next, the equation below shows the relationship between the post normal shock temperature, $T\_2$, and the upstream ambient temperature, $T\_1$. $\backslash frac\; =\; \backslash fracM\_1^2\backslash right)\backslash left(\backslash fracM\_1^2\; -\; 1\backslash right)\}\; +\; \backslash frac\backslash right)\}$ Finally, the ratio of stagnation pressures is shown below where $p\_$ is the upstream stagnation pressure and $p\_$ occurs after the normal shock. The ratio of stagnation temperatures remains constant across a normal shock since the process is adiabatic. $\backslash frac\}\; =\; \backslash left(\backslash fracM\_1^2\}M\_1^2\}\backslash right)^\backslash frac\backslash left(\backslash fracM\_1^2\; -\; \backslash frac\}\backslash right)^\backslash frac$ 抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』 ■ウィキペディアで「Normal shock tables」の詳細全文を読む スポンサード リンク 翻訳と辞書 : 翻訳のためのインターネットリソース Copyright(C) kotoba.ne.jp 1997-2016. All Rights Reserved.