{"id":66983,"date":"2026-10-13T10:46:54","date_gmt":"2026-10-13T07:46:54","guid":{"rendered":"https:\/\/wpcalc.com\/en\/?p=66983"},"modified":"2026-10-13T10:46:54","modified_gmt":"2026-10-13T07:46:54","slug":"hohmann-transfer-calculator","status":"publish","type":"post","link":"https:\/\/wpcalc.com\/en\/physics\/hohmann-transfer-calculator\/","title":{"rendered":"Hohmann Transfer 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\">Find the Delta-V and Transfer Time Between Two Circular Orbits<\/h2><\/div><div class=\"calcdash-favorite group\">\n  <button type=\"button\" class=\"favorite\" id=\"favorite\" data-favorite-id=\"66983\" data-favorite-title=\"Hohmann Transfer\" data-favorite-url=\"https:\/\/wpcalc.com\/en\/physics\/hohmann-transfer-calculator\/\" data-favorite-excerpt=\"Compute the two burns, total delta-v and transfer time of a Hohmann transfer between two coplanar circular orbits. Enter the gravitational parameter and the two orbit radii.\" aria-label=\"Add to Favorites\" data-favorite-icon=\"icon icon-astronomy\">\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\/hohmann-transfer-calculator\/\" method=\"POST\" class=\"calculator\" id=\"calculator-66983\" data-post=\"66983\"><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\">Gravitational parameter (\u03bc)<\/label><div class=\"term\">\u03bc<\/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=\"gravitational_parameter_\" id=\"field-1\" aria-describedby=\"calc-info-1\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 398600.44\" min=\"0\" value=\"398600.4418\"\/><div class=\"grid grid-cols-1\"><select id=\"field-2\" name=\"unit\" aria-label=\"Unit\"><option value=\"km3s2\" selected>km\u00b3\/s\u00b2<\/option><option value=\"m3s2\">m\u00b3\/s\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-1\">\u03bc = G\u00b7M of the central body. Earth = 398,600.44 km\u00b3\/s\u00b2, Moon = 4,902.8, Sun = 1.32712\u00d710\u00b9\u00b9, Mars = 42,828.4 km\u00b3\/s\u00b2.<\/small><\/div><div class=\"field has-term\" id=\"input-2\"><label for=\"field-3\">Initial orbit radius (r\u2081)<\/label><div class=\"term\">r\u2081<\/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=\"initial_orbit_radius_r\" id=\"field-3\" aria-describedby=\"calc-info-3\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 6678\" min=\"0\" value=\"6678\"\/><div class=\"grid grid-cols-1\"><select id=\"field-4\" name=\"unit\" aria-label=\"Unit\"><option value=\"km\" selected>km<\/option><option value=\"m\">m<\/option><option value=\"mi\">mi<\/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\">Radius of the starting circular orbit, measured from the centre of the body (not altitude!). Earth: LEO \u2248 6,678 km, surface \u2248 6,371 km.<\/small><\/div><div class=\"field has-term\" id=\"input-3\"><label for=\"field-5\">Target orbit radius (r\u2082)<\/label><div class=\"term\">r\u2082<\/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=\"target_orbit_radius_r\" id=\"field-5\" aria-describedby=\"calc-info-5\" data-number inputmode=\"decimal\" autocomplete=\"off\" spellcheck=\"false\" placeholder=\"e.g. 42164\" min=\"0\" value=\"42164\"\/><div class=\"grid grid-cols-1\"><select id=\"field-6\" name=\"unit\" aria-label=\"Unit\"><option value=\"km\" selected>km<\/option><option value=\"m\">m<\/option><option value=\"mi\">mi<\/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-5\">Radius of the destination circular orbit. Earth: GEO = 42,164 km, GPS \u2248 26,560 km, Moon&#039;s orbit \u2248 384,400 km.<\/small><\/div><\/fieldset><div class=\"buttons\"><button type=\"submit\" data-text=\"Re-Calculate\" id=\"calculate-button\" data-post=\"66983\">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> Hohmann Transfer Results<\/h3><div class=\"result-box\"><div class=\"field-result is-column\" id=\"output-1\"><span class=\"field-title\"><span>First velocity change (\u0394v\u2081)<\/span><span class=\"result-term\">\u0394v\u2081<\/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>Second velocity change (\u0394v\u2082)<\/span><span class=\"result-term\">\u0394v\u2082<\/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 class=\"field-result is-column\" id=\"output-3\"><span class=\"field-title\"><span>Total delta-v<\/span><span class=\"result-term\">\u0394v<\/span><\/span><span class=\"field-value\" id=\"result-3\"><\/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-4\"><span class=\"field-title\"><span>Transfer time (half of the transfer ellipse)<\/span><span class=\"result-term\">t<\/span><\/span><span class=\"field-value\" id=\"result-4\"><\/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-5\"><span class=\"field-title\"><span>Orbit details and interpretation<\/span><\/span><span class=\"field-value\" id=\"result-5\"><\/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=\"66983\" 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>Hohmann Transfer Formula<\/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\\[ \\Delta v_1 = \\sqrt{\\frac{\\mu}{r_1}} \\left( \\sqrt{\\frac{2r_2}{r_1+r_2}} - 1 \\right), \\qquad \\Delta v_2 = \\sqrt{\\frac{\\mu}{r_2}} \\left( 1 - \\sqrt{\\frac{2r_1}{r_1+r_2}} \\right) \\\\ t = \\pi \\sqrt{\\frac{a^3}{\\mu}}, \\qquad a = \\frac{r_1 + r_2}{2} \\]\n<\/div>\r\n\t<\/figure>\r\n\t<\/p>\n<p><strong>Where:<\/strong><\/p>\n<ul>\n<li>\\(\\mu\\) \u2014 gravitational parameter of the central body, \\(\\mu = GM\\) (km\u00b3\/s\u00b2)<\/li>\n<li>\\(r_1\\) \u2014 radius of the initial circular orbit, measured from the centre of the body (km)<\/li>\n<li>\\(r_2\\) \u2014 radius of the target circular orbit (km)<\/li>\n<li>\\(\\Delta v_1, \\Delta v_2\\) \u2014 velocity changes of the first and second burn (km\/s)<\/li>\n<li>\\(a\\) \u2014 semi-major axis of the transfer ellipse (km)<\/li>\n<li>\\(t\\) \u2014 transfer time, i.e. half the orbital period of the transfer ellipse (s)<\/li>\n<\/ul>\n<p>The first expression gives the burn needed at \\(r_1\\) to enter an ellipse that touches both circular orbits; the second gives the burn half a revolution later at \\(r_2\\) to circularise. The total delta-v is the sum of the two magnitudes, \\(\\Delta v = |\\Delta v_1| + |\\Delta v_2|\\).<\/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>Hohmann Transfer \u2013 Calculation Example<\/h2><\/div>\r\n\r\n<\/p>\n<p><strong>Example:<\/strong> a spacecraft in a 300 km low Earth orbit (radius \\(r_1 = 6678\\) km) is transferred to geostationary orbit (radius \\(r_2 = 42{,}164\\) km). For Earth, \\(\\mu = 398{,}600.44\\) km\u00b3\/s\u00b2.<\/p>\n<p>\\[ \\Delta v_1 = \\sqrt{\\frac{398600.44}{6678}} \\left( \\sqrt{\\frac{2 \\times 42164}{6678 + 42164}} - 1 \\right) = 7.726 \\times 0.3140 = 2.426 \\text{ km\/s} \\]<\/p>\n<p>\\[ \\Delta v_2 = \\sqrt{\\frac{398600.44}{42164}} \\left( 1 - \\sqrt{\\frac{2 \\times 6678}{48842}} \\right) = 3.075 \\times 0.4771 = 1.467 \\text{ km\/s} \\]<\/p>\n<p>\\[ \\Delta v = 2.426 + 1.467 = 3.893 \\text{ km\/s} \\]<\/p>\n<p>\\[ t = \\pi \\sqrt{\\frac{24421^3}{398600.44}} \\approx 18{,}986 \\text{ s} \\approx 5.27 \\text{ h} \\]<\/p>\n<p><strong>Result:<\/strong> the spacecraft burns 2.426 km\/s to enter the transfer ellipse, another 1.467 km\/s to circularise at GEO \u2014 3.893 km\/s in total \u2014 and the transfer itself takes about 5.27 hours (half of the transfer ellipse's 10.55-hour period).<\/p>\n<p>\n\r\n<\/section>\n<h2>How to use the calculator<\/h2>\n<ol>\n<li>Enter the <strong>Gravitational parameter (\u03bc)<\/strong> of the central body and pick the unit (km\u00b3\/s\u00b2 or m\u00b3\/s\u00b2). For Earth use 398,600.44 km\u00b3\/s\u00b2; the field descriptions list values for the Moon, Sun and Mars.<\/li>\n<li>Enter the <strong>Initial orbit radius (r\u2081)<\/strong>. This is the distance from the <em>centre<\/em> of the body, not the altitude. If you only know the altitude, add the body's radius (Earth \u2248 6,371 km) first.<\/li>\n<li>Enter the <strong>Target orbit radius (r\u2082)<\/strong> the same way, and choose km, m or miles for both radii.<\/li>\n<li>Read the results: <strong>First velocity change (\u0394v\u2081)<\/strong>, <strong>Second velocity change (\u0394v\u2082)<\/strong>, <strong>Total delta-v<\/strong>, <strong>Transfer time<\/strong>, plus a details table with the circular and transfer-orbit speeds, the semi-major axis of the transfer ellipse and both orbit periods.<\/li>\n<\/ol>\n<h2>What is a Hohmann transfer?<\/h2>\n<p>A Hohmann transfer moves a spacecraft between two circular orbits that share the same plane using exactly two burns. The spacecraft first fires its engine prograde (or retrograde, when moving to a lower orbit), which raises \u2014 or lowers \u2014 the opposite side of its orbit so that it forms an ellipse tangent to both circles. At the far end of this ellipse, half a revolution later, a second burn adjusts the speed to match the target circular orbit. Because the ellipse touches both orbits exactly once, the geometry is perfectly symmetrical and the burn sizes are as small as geometry allows.<\/p>\n<p>Walter Hohmann described this manoeuvre in 1925, and it was later proven to be the most propellant-efficient transfer between coplanar circular orbits that uses only two impulses. That efficiency is why it became the standard for orbit raising: communications satellites reaching geostationary orbit, and interplanetary probes travelling between planetary orbits around the Sun, all follow Hohmann-type trajectories. The classic Earth-to-Mars transfer, for example, is a Hohmann ellipse around the Sun taking about 8.5 months.<\/p>\n<p>The total delta-v is the real \u201cfuel cost\u201d of the manoeuvre. Combined with the rocket equation, it determines how much propellant the spacecraft must carry, so mission planners compare transfers almost exclusively in km\/s. The transfer time \u2014 half the period of the ellipse \u2014 is the price you pay for that efficiency: a Hohmann transfer is the <em>slowest<\/em> reasonable two-burn route. Faster transfers exist, but they need larger burns and a different trajectory shape.<\/p>\n<p>Note the direction of the manoeuvre when interpreting the results. Going outward (raising the orbit), both burns are accelerations. Going inward, both burns are braking manoeuvres \u2014 the calculator shows their magnitudes, since a braking burn still spends the same amount of propellant.<\/p>\n<h2>Assumptions, limitations and practical tips<\/h2>\n<ul>\n<li><strong>Coplanar circular orbits.<\/strong> If the orbits are inclined relative to each other, plane-change burns are needed on top of the values shown here, and the optimal split of the burns changes.<\/li>\n<li><strong>Impulsive burns.<\/strong> Real engines fire for minutes, not instantaneously, which adds small gravity losses; low-thrust (electric) propulsion uses an entirely different, spiralling trajectory.<\/li>\n<li><strong>Point-mass body, no perturbations.<\/strong> Atmospheric drag in very low orbits, the oblateness of the body and third-body gravity are ignored. In low Earth orbit, <a href=\"https:\/\/wpcalc.com\/en\/physics\/drag-force-calculator\/\">atmospheric drag<\/a> continuously lowers the orbit and must be compensated for separately.<\/li>\n<li><strong>Radii, not altitudes.<\/strong> The most common input mistake is entering the altitude. Radius = altitude + body radius; the default example (300 km altitude \u2192 6,678 km radius) shows the conversion for Earth.<\/li>\n<li><strong>Very large radius ratios.<\/strong> When \\(r_2\/r_1\\) exceeds roughly 11.9, a bi-elliptic transfer (three burns through an intermediate very high orbit) can beat the Hohmann transfer on total delta-v, at the cost of a much longer flight time.<\/li>\n<li><strong>Interplanetary transfers.<\/strong> Use the Sun's \\(\\mu\\) (1.32712\u00d710\u00b9\u00b9 km\u00b3\/s\u00b2) and the orbital radii of the two planets, and remember that the planets must be correctly phased at departure.<\/li>\n<\/ul>\n<p>For quick reference, common gravitational parameters: Earth 398,600.44 km\u00b3\/s\u00b2, the Moon 4,902.8 km\u00b3\/s\u00b2, Mars 42,828.4 km\u00b3\/s\u00b2, and the Sun 1.32712\u00d710\u00b9\u00b9 km\u00b3\/s\u00b2. Useful Earth radii: LEO \u2248 6,678 km, GPS \u2248 26,560 km, GEO = 42,164 km, and the Moon's orbit \u2248 384,400 km \u2014 all measured from Earth's centre.<\/p>\n","protected":false},"excerpt":{"rendered":"<p>Compute the two burns, total delta-v and transfer time of a Hohmann transfer between two coplanar circular orbits. Enter the gravitational parameter and the two orbit radii.<\/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":[89],"class_list":["post-66983","post","type-post","status-publish","format-standard","hentry","category-physics","tag-gravity-space"],"acf":[],"_links":{"self":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66983","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=66983"}],"version-history":[{"count":1,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66983\/revisions"}],"predecessor-version":[{"id":66984,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/posts\/66983\/revisions\/66984"}],"wp:attachment":[{"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/media?parent=66983"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/categories?post=66983"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/wpcalc.com\/en\/wp-json\/wp\/v2\/tags?post=66983"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}