build based on 2defd94

dev/.documenter-siteinfo.json

@@ -1 +1 @@
-{"documenter":{"julia_version":"1.10.0","generation_timestamp":"2024-02-07T11:46:16","documenter_version":"1.2.1"}}
+{"documenter":{"julia_version":"1.10.0","generation_timestamp":"2024-02-07T14:41:55","documenter_version":"1.2.1"}}

dev/aero/geometry/index.html

@@ -102,4 +102,4 @@
 S_{\rm ref}   &\!= (S)_{\rm wing}\\
 {A\hspace{-0.5ex}R}_{\rm ref} &\!= ({A\hspace{-0.5ex}R})_{\rm wing}\\
 c_{\rm ref}   &\!= (c_{\rm ma})_{\rm wing}
-\end{aligned}\]</p><article class="docstring"><header><a class="docstring-article-toggle-button fa-solid fa-chevron-down" href="javascript:;" title="Collapse docstring"></a><a class="docstring-binding" id="TASOPT.aerodynamics.wingsc-NTuple{8, Any}" href="#TASOPT.aerodynamics.wingsc-NTuple{8, Any}"><code>TASOPT.aerodynamics.wingsc</code></a> — <span class="docstring-category">Method</span></header><section><div><pre><code class="language-julia hljs">wingsc(W, CL, qinf, AR, ηsi, bo, λt, λs)</code></pre><p>Sizes wing area, span, root chord from <code>q</code>, <code>CL</code>, <code>W</code>, <code>AR</code> at given point (taken as start-of-cruise in <code>wsize</code>).</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>W::Float64</code>: Aircraft weight.</li><li><code>CL::Float64</code>: Lift coefficient.</li><li><code>qinf::Float64</code>: Freestream dynamic head.</li><li><code>AR::Float64</code>: Wing aspect ratio.</li><li><code>ηsi::Float64</code>: Span fraction of inner wing break (&quot;snag&quot;).</li><li><code>bo::Float64</code>: Wing center box width.</li><li><code>λt::Float64</code>: Outer or &quot;tip&quot; taper ratio of chord.</li><li><code>λs::Float64</code>: Inner or break/&quot;snag&quot; taper ratio of chord.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>S::Float64</code>: Wing planform area (including fuselage carryover).</li><li><code>b::Float64</code>: Wing span.</li><li><code>bs::Float64</code>: Span of inner wing (break/&quot;snag&quot;).</li><li><code>co::Float64</code>: Chord at wing root, &quot;center.&quot;</li></ul></div></details><p>See Sections 2.5 and 3.4.1 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/4d37eb4790f438905acc30e6565e4acb6a94a276/src/aero/wingsc.jl#L1-L24">source</a></section></article></article><nav class="docs-footer"><a class="docs-footer-prevpage" href="../../examples/optimization/">« Multivariable optimization</a><a class="docs-footer-nextpage" href="../lift/">Lift »</a><div class="flexbox-break"></div><p class="footer-message">Powered by <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> and the <a href="https://julialang.org/">Julia Programming Language</a>.</p></nav></div><div class="modal" id="documenter-settings"><div class="modal-background"></div><div class="modal-card"><header class="modal-card-head"><p class="modal-card-title">Settings</p><button class="delete"></button></header><section class="modal-card-body"><p><label class="label">Theme</label><div class="select"><select id="documenter-themepicker"><option value="documenter-light">documenter-light</option><option value="documenter-dark">documenter-dark</option><option value="auto">Automatic (OS)</option></select></div></p><hr/><p>This document was generated with <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> version 1.2.1 on <span class="colophon-date" title="Wednesday 7 February 2024 11:46">Wednesday 7 February 2024</span>. Using Julia version 1.10.0.</p></section><footer class="modal-card-foot"></footer></div></div></div></body></html>
+\end{aligned}\]</p><article class="docstring"><header><a class="docstring-article-toggle-button fa-solid fa-chevron-down" href="javascript:;" title="Collapse docstring"></a><a class="docstring-binding" id="TASOPT.aerodynamics.wingsc-NTuple{8, Any}" href="#TASOPT.aerodynamics.wingsc-NTuple{8, Any}"><code>TASOPT.aerodynamics.wingsc</code></a> — <span class="docstring-category">Method</span></header><section><div><pre><code class="language-julia hljs">wingsc(W, CL, qinf, AR, ηsi, bo, λt, λs)</code></pre><p>Sizes wing area, span, root chord from <code>q</code>, <code>CL</code>, <code>W</code>, <code>AR</code> at given point (taken as start-of-cruise in <code>wsize</code>).</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>W::Float64</code>: Aircraft weight.</li><li><code>CL::Float64</code>: Lift coefficient.</li><li><code>qinf::Float64</code>: Freestream dynamic head.</li><li><code>AR::Float64</code>: Wing aspect ratio.</li><li><code>ηsi::Float64</code>: Span fraction of inner wing break (&quot;snag&quot;).</li><li><code>bo::Float64</code>: Wing center box width.</li><li><code>λt::Float64</code>: Outer or &quot;tip&quot; taper ratio of chord.</li><li><code>λs::Float64</code>: Inner or break/&quot;snag&quot; taper ratio of chord.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>S::Float64</code>: Wing planform area (including fuselage carryover).</li><li><code>b::Float64</code>: Wing span.</li><li><code>bs::Float64</code>: Span of inner wing (break/&quot;snag&quot;).</li><li><code>co::Float64</code>: Chord at wing root, &quot;center.&quot;</li></ul></div></details><p>See Sections 2.5 and 3.4.1 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/2defd94c5b208763d4f4cdedd6a07c1b49911f7c/src/aero/wingsc.jl#L1-L24">source</a></section></article></article><nav class="docs-footer"><a class="docs-footer-prevpage" href="../../examples/optimization/">« Multivariable optimization</a><a class="docs-footer-nextpage" href="../lift/">Lift »</a><div class="flexbox-break"></div><p class="footer-message">Powered by <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> and the <a href="https://julialang.org/">Julia Programming Language</a>.</p></nav></div><div class="modal" id="documenter-settings"><div class="modal-background"></div><div class="modal-card"><header class="modal-card-head"><p class="modal-card-title">Settings</p><button class="delete"></button></header><section class="modal-card-body"><p><label class="label">Theme</label><div class="select"><select id="documenter-themepicker"><option value="documenter-light">documenter-light</option><option value="documenter-dark">documenter-dark</option><option value="auto">Automatic (OS)</option></select></div></p><hr/><p>This document was generated with <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> version 1.2.1 on <span class="colophon-date" title="Wednesday 7 February 2024 14:41">Wednesday 7 February 2024</span>. Using Julia version 1.10.0.</p></section><footer class="modal-card-foot"></footer></div></div></div></body></html>

dev/aero/lift/index.html

@@ -73,7 +73,7 @@
 p_t & \!=\! p_o \, \gamma_t
 \end{aligned}\]</p></div></details><article class="docstring"><header><a class="docstring-article-toggle-button fa-solid fa-chevron-down" href="javascript:;" title="Collapse docstring"></a><a class="docstring-binding" id="TASOPT.aerodynamics.wingpo-NTuple{13, Any}" href="#TASOPT.aerodynamics.wingpo-NTuple{13, Any}"><code>TASOPT.aerodynamics.wingpo</code></a> — <span class="docstring-category">Method</span></header><section><div><pre><code class="language-julia hljs">wingpo(b, bs, bo, 
     λt, λs, γt, γs, 
-    AR, N, W, Lhtail, fLo, fLt)</code></pre><p>Computes wing root (&quot;center&quot;) loading <span>$p_o$</span> to balance the net load.</p><p class="math-container">\[N*W - L_{h tail} \times 2*∫p(η) dy + 2ΔL₀ + 2ΔLₜ = N*W - (L_{htail}).\]</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>b::Float64</code>: Wing span.</li><li><code>bs::Float64</code>: Span of inner wing section.</li><li><code>bo::Float64</code>:  Span of wing box (span at wing root).</li><li><code>λt::Float64</code>, <code>λs::Float64</code> : Wing chord taper ratios at tip and break (&quot;snag&quot;), respectively.</li><li><code>γt::Float64</code>,<code>γs::Float64</code> : Wing lift distribution &quot;taper&quot; ratios for outer and inner wing sections, respectively.</li><li><code>AR::Float64</code>, <code>N::Float64</code>, <code>W::Float64</code>, <code>Lhtail</code> : Aspect ratio, Load factor, weight and H-tail lift.</li><li><code>fLo::Float64</code>, <code>fLt::Float64</code> : Wing root and tip load adjustment factors.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>po::Float64</code>: Wing root loading magnitude.</li></ul></div></details><p>See Section 2.6.2 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/4d37eb4790f438905acc30e6565e4acb6a94a276/src/aero/wingpo.jl#L1-L26">source</a></section></article><article class="docstring"><header><a class="docstring-article-toggle-button fa-solid fa-chevron-down" href="javascript:;" title="Collapse docstring"></a><a class="docstring-binding" id="TASOPT.aerodynamics.wingcl-NTuple{16, Any}" href="#TASOPT.aerodynamics.wingcl-NTuple{16, Any}"><code>TASOPT.aerodynamics.wingcl</code></a> — <span class="docstring-category">Method</span></header><section><div><pre><code class="language-julia hljs">wingcl(b,bs,bo,
+    AR, N, W, Lhtail, fLo, fLt)</code></pre><p>Computes wing root (&quot;center&quot;) loading <span>$p_o$</span> to balance the net load.</p><p class="math-container">\[N*W - L_{h tail} \times 2*∫p(η) dy + 2ΔL₀ + 2ΔLₜ = N*W - (L_{htail}).\]</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>b::Float64</code>: Wing span.</li><li><code>bs::Float64</code>: Span of inner wing section.</li><li><code>bo::Float64</code>:  Span of wing box (span at wing root).</li><li><code>λt::Float64</code>, <code>λs::Float64</code> : Wing chord taper ratios at tip and break (&quot;snag&quot;), respectively.</li><li><code>γt::Float64</code>,<code>γs::Float64</code> : Wing lift distribution &quot;taper&quot; ratios for outer and inner wing sections, respectively.</li><li><code>AR::Float64</code>, <code>N::Float64</code>, <code>W::Float64</code>, <code>Lhtail</code> : Aspect ratio, Load factor, weight and H-tail lift.</li><li><code>fLo::Float64</code>, <code>fLt::Float64</code> : Wing root and tip load adjustment factors.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>po::Float64</code>: Wing root loading magnitude.</li></ul></div></details><p>See Section 2.6.2 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/2defd94c5b208763d4f4cdedd6a07c1b49911f7c/src/aero/wingpo.jl#L1-L26">source</a></section></article><article class="docstring"><header><a class="docstring-article-toggle-button fa-solid fa-chevron-down" href="javascript:;" title="Collapse docstring"></a><a class="docstring-binding" id="TASOPT.aerodynamics.wingcl-NTuple{16, Any}" href="#TASOPT.aerodynamics.wingcl-NTuple{16, Any}"><code>TASOPT.aerodynamics.wingcl</code></a> — <span class="docstring-category">Method</span></header><section><div><pre><code class="language-julia hljs">wingcl(b,bs,bo,
     λt,λs,γt,γs,
     sweep,AR,CL,CLhtail,fLo,fLt,
-    duo,dus,dut)</code></pre><p>Calculates section cl at  eta = ηo,ηs,1</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>b::Float64</code>, <code>bs::Float64</code>, <code>bo::Float64</code>: Span of wing, inner wing section (up to &quot;snag&quot;), and wing root, respectively.</li><li><code>λt::Float64</code>, <code>λs::Float64</code>: Wing chord taper ratios at tip and break (&quot;snag&quot;), respectively.</li><li><code>γt::Float64</code>, <code>γs::Float64</code>: Wing lift distribution &quot;taper&quot; ratios for outer and inner wing sections, respectively.</li><li><code>sweep::Float64</code>: Wing sweep for reference axis.</li><li><code>AR::Float64</code>: Wing aspect ratio, <span>$AR = b^2/S$</span>.</li><li><code>CL::Float64</code>, <code>CLhtail::Float64</code>: Overall lift coefficient of wing and horizontal tail, respectively.</li><li><code>fLo::Float64</code>, <code>fLt::Float64</code>: Correction factors for lift of wingbox and tip.</li><li><code>duo::Float64</code>, <code>dus::Float64</code>, <code>dut::Float64</code>: Velocity-change fractions at wing root, break (&quot;snag&quot;), and tip due to fuselage flow.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>clo::Float64</code>, <code>cls::Float64</code>, <code>clt::Float64</code>: Section lift coefficient at root, wing break (&quot;snag&quot;), and tip.</li></ul></div></details><p>See Sections 2.5 and 2.6 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>. Called by <code>cdsum!</code>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/4d37eb4790f438905acc30e6565e4acb6a94a276/src/aero/wingpo.jl#L51-L74">source</a></section></article></article><nav class="docs-footer"><a class="docs-footer-prevpage" href="../geometry/">« Geometry</a><a class="docs-footer-nextpage" href="../drag/">Drag »</a><div class="flexbox-break"></div><p class="footer-message">Powered by <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> and the <a href="https://julialang.org/">Julia Programming Language</a>.</p></nav></div><div class="modal" id="documenter-settings"><div class="modal-background"></div><div class="modal-card"><header class="modal-card-head"><p class="modal-card-title">Settings</p><button class="delete"></button></header><section class="modal-card-body"><p><label class="label">Theme</label><div class="select"><select id="documenter-themepicker"><option value="documenter-light">documenter-light</option><option value="documenter-dark">documenter-dark</option><option value="auto">Automatic (OS)</option></select></div></p><hr/><p>This document was generated with <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> version 1.2.1 on <span class="colophon-date" title="Wednesday 7 February 2024 11:46">Wednesday 7 February 2024</span>. Using Julia version 1.10.0.</p></section><footer class="modal-card-foot"></footer></div></div></div></body></html>
+    duo,dus,dut)</code></pre><p>Calculates section cl at  eta = ηo,ηs,1</p><details class="admonition is-details"><summary class="admonition-header">🔃 Inputs and Outputs</summary><div class="admonition-body"><p><strong>Inputs:</strong></p><ul><li><code>b::Float64</code>, <code>bs::Float64</code>, <code>bo::Float64</code>: Span of wing, inner wing section (up to &quot;snag&quot;), and wing root, respectively.</li><li><code>λt::Float64</code>, <code>λs::Float64</code>: Wing chord taper ratios at tip and break (&quot;snag&quot;), respectively.</li><li><code>γt::Float64</code>, <code>γs::Float64</code>: Wing lift distribution &quot;taper&quot; ratios for outer and inner wing sections, respectively.</li><li><code>sweep::Float64</code>: Wing sweep for reference axis.</li><li><code>AR::Float64</code>: Wing aspect ratio, <span>$AR = b^2/S$</span>.</li><li><code>CL::Float64</code>, <code>CLhtail::Float64</code>: Overall lift coefficient of wing and horizontal tail, respectively.</li><li><code>fLo::Float64</code>, <code>fLt::Float64</code>: Correction factors for lift of wingbox and tip.</li><li><code>duo::Float64</code>, <code>dus::Float64</code>, <code>dut::Float64</code>: Velocity-change fractions at wing root, break (&quot;snag&quot;), and tip due to fuselage flow.</li></ul><p><strong>Outputs:</strong></p><ul><li><code>clo::Float64</code>, <code>cls::Float64</code>, <code>clt::Float64</code>: Section lift coefficient at root, wing break (&quot;snag&quot;), and tip.</li></ul></div></details><p>See Sections 2.5 and 2.6 of the <a href="../../misc/dreladocs/#dreladocs">TASOPT Technical Desc</a>. Called by <code>cdsum!</code>.</p></div><a class="docs-sourcelink" target="_blank" href="https://github.com/MIT-LAE/TASOPT.jl/blob/2defd94c5b208763d4f4cdedd6a07c1b49911f7c/src/aero/wingpo.jl#L51-L74">source</a></section></article></article><nav class="docs-footer"><a class="docs-footer-prevpage" href="../geometry/">« Geometry</a><a class="docs-footer-nextpage" href="../drag/">Drag »</a><div class="flexbox-break"></div><p class="footer-message">Powered by <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> and the <a href="https://julialang.org/">Julia Programming Language</a>.</p></nav></div><div class="modal" id="documenter-settings"><div class="modal-background"></div><div class="modal-card"><header class="modal-card-head"><p class="modal-card-title">Settings</p><button class="delete"></button></header><section class="modal-card-body"><p><label class="label">Theme</label><div class="select"><select id="documenter-themepicker"><option value="documenter-light">documenter-light</option><option value="documenter-dark">documenter-dark</option><option value="auto">Automatic (OS)</option></select></div></p><hr/><p>This document was generated with <a href="https://github.com/JuliaDocs/Documenter.jl">Documenter.jl</a> version 1.2.1 on <span class="colophon-date" title="Wednesday 7 February 2024 14:41">Wednesday 7 February 2024</span>. Using Julia version 1.10.0.</p></section><footer class="modal-card-foot"></footer></div></div></div></body></html>