{"id":66927,"date":"2026-10-13T10:31:52","date_gmt":"2026-10-13T07:31:52","guid":{"rendered":"https:\/\/wpcalc.com\/en\/?p=66927"},"modified":"2026-10-13T10:31:52","modified_gmt":"2026-10-13T07:31:52","slug":"lift-force-calculator","status":"publish","type":"post","link":"https:\/\/wpcalc.com\/en\/physics\/lift-force-calculator\/","title":{"rendered":"Lift Force Calculator"},"content":{"rendered":"<section class=\"not-prose calculator-box\" aria-labelledby=\"calculator-title\"><div class=\"flex items-baseline sm:items-center justify-between gap-2 sm:gap-3\"><div class=\"flex flex-col sm:flex-row sm:items-center gap-2\"><span class=\"icon icon-calculator text-primary-700! text-base! dark:text-primary-300!\" aria-hidden=\"true\"><\/span><h2 id=\"calculator-title\" class=\"text-lg font-display font-bold\">Estimate Aerodynamic Lift from Speed and Wing Characteristics<\/h2><\/div><div class=\"calcdash-favorite group\">\n  <button type=\"button\" class=\"favorite\" id=\"favorite\" data-favorite-id=\"66927\" data-favorite-title=\"Lift Force\" data-favorite-url=\"https:\/\/wpcalc.com\/en\/physics\/lift-force-calculator\/\" data-favorite-excerpt=\"Calculate aerodynamic lift force from fluid density, flow speed, lift coefficient, and wing area. Enter your values, pick units, and get lift in newtons, lbf, and kgf instantly.\" aria-label=\"Add to Favorites\" data-favorite-icon=\"icon icon-physic\">\n    <span class=\"icon icon-shape-star-empty\" aria-hidden=\"true\"><\/span>\n  <\/button>\n  <div class=\"calcdash-favorite__tip\" aria-hidden=\"true\">\n   <span class=\"favorite-tooltip\" id=\"favorite-tooltip\"><\/span>\n  <\/div>\n  <span class=\"sr-only\" role=\"status\" id=\"favorite-status\"><\/span>\n<\/div><\/div><form action=\"https:\/\/wpcalc.com\/en\/physics\/lift-force-calculator\/\" method=\"POST\" class=\"calculator\" id=\"calculator-66927\" data-post=\"66927\"><fieldset class=\"fieldset-input is-1\"><legend class=\"sr-only\">Input Fields<\/legend><div class=\"field has-term\" id=\"input-1\"><label for=\"field-1\">Fluid density (\u03c1)<\/label><div class=\"term\">\u03c1<\/div>  <div class=\"absolute bottom-0 left-16 top-8 w-2 h-0.5 bg-blue-500\"><\/div><div class=\"field-group\"><input type=\"text\" name=\"fluid_density_\" id=\"field-1\" aria-describedby=\"calc-info-1\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 1.225\" min=\"0\" value=\"1.225\"\/><div class=\"grid grid-cols-1\"><select id=\"field-2\" name=\"unit\" aria-label=\"Unit\"><option value=\"kgm3\" selected>kg\/m\u00b3<\/option><option value=\"slugft3\">slug\/ft\u00b3<\/option><option value=\"gl\">g\/L<\/option><\/select><svg class=\"pointer-events-none col-start-1 row-start-1 mr-2 size-5 self-center justify-self-end text-gray-500 sm:size-4\" viewBox=\"0 0 16 16\" fill=\"currentColor\" aria-hidden=\"true\" data-slot=\"icon\">\n              <path fill-rule=\"evenodd\" d=\"M4.22 6.22a.75.75 0 0 1 1.06 0L8 8.94l2.72-2.72a.75.75 0 1 1 1.06 1.06l-3.25 3.25a.75.75 0 0 1-1.06 0L4.22 7.28a.75.75 0 0 1 0-1.06Z\" clip-rule=\"evenodd\" \/>\n            <\/svg><\/div><\/div><small id=\"calc-info-1\">Density of the surrounding fluid. Standard sea-level air is 1.225 kg\/m\u00b3 (0.002377 slug\/ft\u00b3); water is about 1000 kg\/m\u00b3.<\/small><\/div><div class=\"field has-term\" id=\"input-2\"><label for=\"field-3\">Flow speed (v)<\/label><div class=\"term\">v<\/div>  <div class=\"absolute bottom-0 left-16 top-8 w-2 h-0.5 bg-blue-500\"><\/div><div class=\"field-group\"><input type=\"text\" name=\"flow_speed_v\" id=\"field-3\" aria-describedby=\"calc-info-3\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 100\" min=\"0\" value=\"100\"\/><div class=\"grid grid-cols-1\"><select id=\"field-4\" name=\"unit\" aria-label=\"Unit\"><option value=\"ms\">m\/s<\/option><option value=\"kmh\" selected>km\/h<\/option><option value=\"mph\">mph<\/option><option value=\"fts\">ft\/s<\/option><option value=\"kn\">knots<\/option><\/select><svg class=\"pointer-events-none col-start-1 row-start-1 mr-2 size-5 self-center justify-self-end text-gray-500 sm:size-4\" viewBox=\"0 0 16 16\" fill=\"currentColor\" aria-hidden=\"true\" data-slot=\"icon\">\n              <path fill-rule=\"evenodd\" d=\"M4.22 6.22a.75.75 0 0 1 1.06 0L8 8.94l2.72-2.72a.75.75 0 1 1 1.06 1.06l-3.25 3.25a.75.75 0 0 1-1.06 0L4.22 7.28a.75.75 0 0 1 0-1.06Z\" clip-rule=\"evenodd\" \/>\n            <\/svg><\/div><\/div><small id=\"calc-info-3\">Speed of the wing relative to the fluid (true airspeed for aircraft).<\/small><\/div><div class=\"field has-term\" id=\"input-3\"><label for=\"field-5\">Lift coefficient (C\u1d3f)<\/label><div class=\"term\">C\u1d3f<\/div>  <div class=\"absolute bottom-0 left-16 top-8 w-2 h-0.5 bg-blue-500\"><\/div><input type=\"text\" name=\"lift_coefficient_c\" id=\"field-5\" aria-describedby=\"calc-info-5\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 0.5\" min=\"0\" max=\"10\" value=\"0.5\"\/><small id=\"calc-info-5\">Dimensionless coefficient from the airfoil\/wing data. Typical cruise values are 0.2\u20130.8; a flat plate at a small angle is roughly 2\u03c0\u00b7\u03b1 (\u03b1 in radians).<\/small><\/div><div class=\"field has-term\" id=\"input-4\"><label for=\"field-6\">Reference area (A)<\/label><div class=\"term\">A<\/div>  <div class=\"absolute bottom-0 left-16 top-8 w-2 h-0.5 bg-blue-500\"><\/div><div class=\"field-group\"><input type=\"text\" name=\"reference_area_a\" id=\"field-6\" aria-describedby=\"calc-info-6\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 25\" min=\"0\" value=\"25\"\/><div class=\"grid grid-cols-1\"><select id=\"field-7\" name=\"unit\" aria-label=\"Unit\"><option value=\"m2\" selected>m\u00b2<\/option><option value=\"ft2\">ft\u00b2<\/option><option value=\"cm2\">cm\u00b2<\/option><option value=\"in2\">in\u00b2<\/option><\/select><svg class=\"pointer-events-none col-start-1 row-start-1 mr-2 size-5 self-center justify-self-end text-gray-500 sm:size-4\" viewBox=\"0 0 16 16\" fill=\"currentColor\" aria-hidden=\"true\" data-slot=\"icon\">\n              <path fill-rule=\"evenodd\" d=\"M4.22 6.22a.75.75 0 0 1 1.06 0L8 8.94l2.72-2.72a.75.75 0 1 1 1.06 1.06l-3.25 3.25a.75.75 0 0 1-1.06 0L4.22 7.28a.75.75 0 0 1 0-1.06Z\" clip-rule=\"evenodd\" \/>\n            <\/svg><\/div><\/div><small id=\"calc-info-6\">Wing planform area (or projected surface area of the lifting body).<\/small><\/div><\/fieldset><div class=\"buttons\"><button type=\"submit\" data-text=\"Re-Calculate\" id=\"calculate-button\" data-post=\"66927\">Calculate<\/button><button type=\"reset\">Reset<\/button><\/div><div class=\"field is-checkbox hidden!\" id=\"field-auto-calc\"><input type=\"checkbox\" id=\"auto-calc\"><label for=\"auto-calc\">Calculate automatically<\/label><small>If enabled, the result will update automatically when you change any value.<\/small><\/div><div class=\"fieldset-result is-hidden\" aria-labelledby=\"result-title\" aria-live=\"polite\" role=\"region\"> <h3 class=\"result-title bg-gradient-to-r from-primary-50 to-gray-50 dark:from-primary-900 dark:to-gray-800\" id=\"result-title\"><span class=\"icon icon-s-pulse\" aria-hidden=\"true\"><\/span> Lift Force Results<\/h3><div class=\"result-box\"><div class=\"field-result is-column\" id=\"output-1\"><span class=\"field-title\"><span>Lift force (L)<\/span><span class=\"result-term\">L<\/span><\/span><span class=\"field-value\" id=\"result-1\"><\/span><button type=\"button\" class=\"copy-result\" data-tooltip=\"Copy Result\" aria-label=\"Copy Result\"><span class=\"copy-icon icon icon-document-copy\" aria-hidden=\"true\"><\/span><\/button><\/div><div class=\"field-result is-column\" id=\"output-2\"><span class=\"field-title\"><span>Dynamic pressure and intermediate values<\/span><\/span><span class=\"field-value\" id=\"result-2\"><\/span><button type=\"button\" class=\"copy-result\" data-tooltip=\"Copy Result\" aria-label=\"Copy Result\"><span class=\"copy-icon icon icon-document-copy\" aria-hidden=\"true\"><\/span><\/button><\/div><\/div><div class=\"result-actions\"><button type=\"button\" class=\"copy-link\"><svg viewBox=\"0 0 20 20\" fill=\"currentColor\" aria-hidden=\"true\"><path d=\"M12.232 4.232a2.5 2.5 0 0 1 3.536 3.536l-1.225 1.224a.75.75 0 0 0 1.061 1.06l1.224-1.224a4 4 0 0 0-5.656-5.656l-3 3a4 4 0 0 0 .225 5.865.75.75 0 0 0 .977-1.138 2.5 2.5 0 0 1-.142-3.667l3-3Z\"\/><path d=\"M11.603 7.963a.75.75 0 0 0-.977 1.138 2.5 2.5 0 0 1 .142 3.667l-3 3a2.5 2.5 0 0 1-3.536-3.536l1.225-1.224a.75.75 0 0 0-1.061-1.06l-1.224 1.224a4 4 0 1 0 5.656 5.656l3-3a4 4 0 0 0-.225-5.865Z\"\/><\/svg><span class=\"copy-link__text\">Copy link to this calculation<\/span><\/button><span class=\"sr-only\" role=\"status\" id=\"copy-link-status\"><\/span><\/div><\/div><a href=\"#respond\" class=\"hidden transition-opacity duration-300 opacity-0 w-50 text-sm justify-center items-center gap-2 px-4 py-2 rounded bg-gray-200 text-gray-700 hover:bg-gray-300\" id=\"leave-comment\"><span class=\"icon icon-comments\" aria-hidden=\"true\"><\/span>Leave a Comment<\/a><\/form><\/section><section id=\"calc-reactions\" class=\"not-prose hidden my-12 bg-gradient-to-r from-primary-50 to-gray-50 border border-indigo-100 rounded-xl px-6 py-4 shadow-sm\" data-post=\"66927\" aria-live=\"polite\" aria-labelledby=\"calc-reactions-title\"><p id=\"calc-reactions-title\" class=\"text-sm text-gray-500 text-center mb-2\">How did this result make you feel?<\/p><div role=\"group\" aria-labelledby=\"calc-reactions-title\" class=\"grid grid-cols-3 sm:flex sm:flex-row sm:justify-around gap-4 sm:items-center sm:flex-wrap\"><button type=\"button\" aria-pressed=\"false\" class=\"reaction-btn flex flex-col items-center gap-1 text-sm text-gray-700 hover:text-primary-600 cursor-pointer transition-transform hover:scale-105\" data-reaction=\"like\"><span class=\"reaction-count\" data-reaction-count=\"like\">0<\/span><span class=\"reaction text-3xl\" aria-hidden=\"true\">\ud83d\ude00 <\/span><span class=\"reaction-description font-medium\">Like <\/span><\/button><button type=\"button\" aria-pressed=\"false\" class=\"reaction-btn flex flex-col items-center gap-1 text-sm text-gray-700 hover:text-primary-600 cursor-pointer transition-transform hover:scale-105\" data-reaction=\"helpful\"><span class=\"reaction-count\" data-reaction-count=\"helpful\">0<\/span><span class=\"reaction text-3xl\" aria-hidden=\"true\">\ud83d\udca1 <\/span><span class=\"reaction-description font-medium\">Helpful <\/span><\/button><button type=\"button\" aria-pressed=\"false\" class=\"reaction-btn flex flex-col items-center gap-1 text-sm text-gray-700 hover:text-primary-600 cursor-pointer transition-transform hover:scale-105\" data-reaction=\"confused\"><span class=\"reaction-count\" data-reaction-count=\"confused\">0<\/span><span class=\"reaction text-3xl\" aria-hidden=\"true\">\ud83d\ude15 <\/span><span class=\"reaction-description font-medium\">Confused <\/span><\/button><button type=\"button\" aria-pressed=\"false\" class=\"reaction-btn flex flex-col items-center gap-1 text-sm text-gray-700 hover:text-primary-600 cursor-pointer transition-transform hover:scale-105\" data-reaction=\"disappointed\"><span class=\"reaction-count\" data-reaction-count=\"disappointed\">0<\/span><span class=\"reaction text-3xl\" aria-hidden=\"true\">\ud83d\ude1e <\/span><span class=\"reaction-description font-medium\">Disappointed <\/span><\/button><button type=\"button\" aria-pressed=\"false\" class=\"reaction-btn flex flex-col items-center gap-1 text-sm text-gray-700 hover:text-primary-600 cursor-pointer transition-transform hover:scale-105\" data-reaction=\"inaccurate\"><span class=\"reaction-count\" data-reaction-count=\"inaccurate\">0<\/span><span class=\"reaction text-3xl\" aria-hidden=\"true\">\u274c <\/span><span class=\"reaction-description font-medium\">Inaccurate <\/span><\/button><\/div><div id=\"reaction-message\" class=\"hidden mt-8 rounded-md border border-primary-100 bg-white\/50 backdrop-blur-sm px-4 py-2 text-sm text-center shadow-sm\"><\/div><\/section><div class=\"calcdash-ad not-prose calcdash-ad--calc_result calcdash-ad--in-article\"><ins class=\"adsbygoogle\" style=\"display:block\" data-ad-client=\"ca-pub-1721569815777345\" data-ad-slot=\"6317458308\" data-ad-layout=\"in-article\" data-ad-format=\"fluid\"><\/ins><script>(adsbygoogle = window.adsbygoogle || []).push({});<\/script><\/div>\n<style id=\"wpcoderpro-inline-1\">.formula-box {\r\n\tborder-bottom: none !important;\r\n}<\/style><section class=\"formula-box\" aria-labelledby=\"formula-title\">\r\n\t<div id=\"formula-title\" class=\"not-prose font-display mb-4\"><span class=\"icon icon-formula\" aria-hidden=\"true\"><\/span><h2>Lift Force<\/h2><\/div>\r\n\t<figure class=\"not-prose formula\">\r\n\t\t<figcaption class=\"formula-title\">Formula<\/figcaption>\r\n\t\t<div class=\"text-base text-gray-800\" id=\"formula\">\n\\[ L = \\tfrac{1}{2}\\, \\rho\\, v^{2}\\, C_L\\, A = q\\, C_L\\, A, \\quad q = \\tfrac{1}{2}\\, \\rho\\, v^{2} \\]\n<\/div>\r\n\t<\/figure>\r\n\t<\/p>\n<p><strong>Where:<\/strong><\/p>\n<ul>\n<li>\\(L\\) \u2014 lift force (N)<\/li>\n<li>\\(\\rho\\) \u2014 fluid density (kg\/m\u00b3)<\/li>\n<li>\\(v\\) \u2014 flow speed, i.e. the speed of the wing relative to the fluid (m\/s)<\/li>\n<li>\\(C_L\\) \u2014 lift coefficient (dimensionless)<\/li>\n<li>\\(A\\) \u2014 reference area, usually the wing planform area (m\u00b2)<\/li>\n<li>\\(q\\) \u2014 dynamic pressure (Pa)<\/li>\n<\/ul>\n<p>The equation states that lift equals the dynamic pressure of the flow multiplied by the reference area and by a dimensionless coefficient that captures the airfoil shape and angle of attack. Because speed enters squared, doubling the speed quadruples the lift.<\/p>\n<p>\r\n<\/section>\n<style id=\"wpcoderpro-inline-459\">.calculation-box {\r\n\tborder-bottom: none !important;\r\n}<\/style><section id=\"calculation\" class=\"calculation-box\" aria-labelledby=\"calculation-title\">\r\n\t<div id=\"calculation-title\" class=\"not-prose font-display\"><span class=\"icon icon-unordered-list\" aria-hidden=\"true\"><\/span><h2>Lift Force \u2013 Calculation Example<\/h2><\/div>\r\n\r\n<\/p>\n<p><strong>Example:<\/strong> a light aircraft cruises at 100 km\/h in standard sea-level air with a wing area of 25 m\u00b2 and a lift coefficient of 0.5.<\/p>\n<p>\\[ v = \\frac{100}{3.6} = 27.78\\ \\text{m\/s} \\]<\/p>\n<p>\\[ q = \\tfrac{1}{2} \\cdot 1.225 \\cdot 27.78^{2} = 472.6\\ \\text{Pa} \\]<\/p>\n<p>\\[ L = 472.6 \\cdot 0.5 \\cdot 25 = 5908\\ \\text{N} \\]<\/p>\n<p><strong>Result:<\/strong> the wing generates about 5908 N (5.91 kN, \u2248 1328 lbf, \u2248 602 kgf) of lift \u2014 enough to support roughly 602 kg in Earth's gravity.<\/p>\n<p>\n\r\n<\/section>\n<h2>How to use the calculator<\/h2>\n<ol>\n<li>Enter the <strong>Fluid density (\u03c1)<\/strong> of the surrounding medium. Standard sea-level air is 1.225 kg\/m\u00b3; select kg\/m\u00b3, slug\/ft\u00b3, or g\/L as the unit.<\/li>\n<li>Enter the <strong>Flow speed (v)<\/strong> \u2014 the speed of the wing through the fluid \u2014 and choose m\/s, km\/h, mph, ft\/s, or knots.<\/li>\n<li>Enter the <strong>Lift coefficient (C\u1d3f)<\/strong> from airfoil or wing data. Typical cruise values are 0.2\u20130.8.<\/li>\n<li>Enter the <strong>Reference area (A)<\/strong>, the wing planform area, in m\u00b2, ft\u00b2, cm\u00b2, or in\u00b2.<\/li>\n<li>Read the results: lift force in newtons, kilonewtons, pound-force, and kilogram-force, plus the dynamic pressure and all intermediate values converted to SI units.<\/li>\n<\/ol>\n<h2>What is lift force?<\/h2>\n<p>Lift is the force exerted by a moving fluid on a body, directed perpendicular to the oncoming flow. On an aircraft wing, the air flowing over the curved upper surface travels faster than the air below, producing a pressure difference; the net upward push is lift. It is what keeps airplanes, gliders, and helicopters airborne, and it also acts on sailboat sails, racing car wings (inverted, to press the car down), and wind turbine blades.<\/p>\n<p>The standard lift equation bundles the physics into three factors. The dynamic pressure \\(q = \\tfrac{1}{2}\\rho v^2\\) measures how much momentum the flow carries per unit area \u2014 it grows with the square of speed, which is why takeoff speed matters so much. The reference area \\(A\\) scales the force with the size of the wing. The lift coefficient \\(C_L\\) summarizes everything about shape and orientation: the airfoil profile, the angle of attack, and the flow conditions. Increasing the angle of attack raises \\(C_L\\) until the wing stalls, at which point it drops sharply.<\/p>\n<p>To interpret the result, compare the lift with the weight it must overcome. In the example above, 5.9 kN of lift supports about 602 kg; a 600 kg aircraft at those conditions would fly in level flight. If lift exceeds weight, the aircraft climbs; if it is less, the aircraft descends. Since the calculator also reports dynamic pressure, you can see directly how much of the force comes from speed alone versus wing size and coefficient.<\/p>\n<h2>Assumptions, limitations, and tips<\/h2>\n<ul>\n<li><strong>Incompressible flow:<\/strong> the formula assumes air density does not change as it flows around the wing. This is reliable up to roughly Mach 0.3 (about 100 m\/s at sea level). At higher speeds, compressibility increases the effective dynamic pressure and the simple result becomes an underestimate.<\/li>\n<li><strong>Steady, level flow:<\/strong> unsteady effects such as gusts, maneuvers, and rapid pitch changes are not captured.<\/li>\n<li><strong>Lift coefficient limits:<\/strong> a plain wing section without high-lift devices rarely exceeds \\(C_L \\approx 1.5\\) before stalling. If your entered value is higher, the calculator flags it \u2014 flaps, slats, or ground effect are then implied.<\/li>\n<li><strong>Density changes with altitude:<\/strong> air density drops with height (about 1.225 kg\/m\u00b3 at sea level, roughly 0.9 kg\/m\u00b3 at 3 km). Use the density at your actual altitude; if you need it from other properties, the <a href=\"https:\/\/wpcalc.com\/en\/physics\/density-calculator\/\">Density calculator<\/a> can help.<\/li>\n<li><strong>Works in water too:<\/strong> hydrofoils and boat rudders follow the same equation \u2014 just enter a water density near 1000 kg\/m\u00b3 and the flow speed underwater.<\/li>\n<li><strong>Reference area consistency:<\/strong> always use the same definition of area that your \\(C_L\\) data is based on (usually the wing planform area for aircraft).<\/li>\n<\/ul>\n<p>Since dynamic pressure is central to this calculation, the <a href=\"https:\/\/wpcalc.com\/en\/physics\/pressure-calculator\/\">Pressure calculator<\/a> is useful for related conversions, and once drag enters the picture, the <a href=\"https:\/\/wpcalc.com\/en\/physics\/terminal-velocity-calculator\/\">Terminal Velocity calculator<\/a> shows how lift and drag balance out in a steady descent.<\/p>\n","protected":false},"excerpt":{"rendered":"<p>Calculate aerodynamic lift force from fluid density, flow speed, lift coefficient, and wing area. Enter your values, pick units, and get lift in newtons, lbf, and kgf instantly.<\/p>\n","protected":false},"author":3168,"featured_media":0,"comment_status":"open","ping_status":"","sticky":false,"template":"","format":"standard","meta":{"_acf_changed":false,"footnotes":""},"categories":[62],"tags":[73],"class_list":["post-66927","post","type-post","status-publish","format-standard","hentry","category-physics","tag-mechanics"],"acf":[],"_links":{"self":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66927","targetHints":{"allow":["GET"]}}],"collection":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/users\/3168"}],"replies":[{"embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/comments?post=66927"}],"version-history":[{"count":1,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66927\/revisions"}],"predecessor-version":[{"id":66928,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66927\/revisions\/66928"}],"wp:attachment":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/media?parent=66927"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/categories?post=66927"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/tags?post=66927"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}