In this article, this effect can be calculated with a calculation form. The calculation is verified by means of a real flight. In addition, all the formulas used are listed and explained.
Deutsche Version: Zentrifugal und Gravitationsbeschleunigung in einem Flugzeug
See Legend for a description of the fields. Set GS = 0 if you want to compute the weight of the test mass for some not moving location. If you set GS = 0, the centrifugal acceleration is calculated with the formulas for a stationary object rotating with the earth! Use the Lat and Alt to specify this fixed location then. The results of this calculation are shown in the right column.
JavaScript for the Calculation Form: Centrifugal and Gravitational Acceleration in an Aircraft
In the following videos Wolfie (a pilot) weighs a test mass on different locations on the earth and in airplanes flying in different directions. The test mass gains and looses weight according to the calculations on this page:
Real evidence that aircraft follow the Earth's curvature.
The Eötvös effect observed in aircraft  how does it affect Gravity?
by wolfie6020; april 2017
The following table compares the magnitudes of the most varied influences on the gravitational acceleration. The first 5 influences are taken into account in the calculations obove.
Value m/s^{2}  Value / 9,806  Description 

9,806  1  Gravitation: Mean effective gravitational acceleration on earth 
0,099  0,010  Aircraft: Centrifugal acceleration in an aircraft at a speed of about 500 kt with a strong tailwind of about 100 kt, direction of flight is east on the equator at an altitude of 12,5 km 
0,034  0,003 5  Max Centrifugal: Amount of centrifugal acceleration at the equator as a part of the effective gravitational acceleration 
0,026  0,002 64  Latitude: Maximum variation of the mean gravitational acceleration depending on latitude: plus at the poles, minus at the equator 
0,003  0,000 3  Altitude: Reduction of effective gravitational acceleration per 1 000 m altitude 
0,002  0,000 204  Geoid: Maximum Geoid variation 
0,001  0,000 102  Range of the maximum Geoid variations on GeoidMaps [1] 
0,000 5  0,000 050  Maximum Range of the Geoid variations on most places on earth +30 mGal correspond to −100 m = −330 ft altitude. 100 mGal = 0,001 m/s^{2}. 
0,000 14  0,000 014  Air Density: Apparent increase of gravitation per 1 000 m altitude due to air density decrease (buoyancy) for an iron weight with a density of 7 874 kg/m^{3} 
0,000 062  0,000 006 3  Coriolis: Maximum influence of the CorriolisEffect at the poles on an airspeed of 480 kt, if the airplane follows a great circle on the surface of the earth. On the equator the influence is 0 [2]. 
0,000 001 63  0,000 000 166  Moon+Sun: Maximum influence of gravitation of the moon and sun combined [3] 
0,000 001 13  0,000 000 115  Moon: Maximum influence of gravitation of the moon 
0,000 000 50  0,000 000 051  Sun: Maximum influence of gravitation of the sun 
[1] World map with the geoid variation in gravitation (PDF)
The calculations are based on an ellipsoid. The real shape of the earth varies from place to place. Therefore, gravitation also varies accordingly. The variation, however, is less than ±0,01% of gravitation at most of the places on earth.
If the deviation of the gravitation of the geoid from the ellipsoid is known, you can consider this in the calculation form by adding a correction value to Alt: +30 mGal → −100 m = −330 ft
[2] Influence of the CoriolisEffect:
(1) 
c = \sqrt{ g^2 + {c_\mathrm{H}}^2 }  g
 
c_\mathrm{H} = 2 \cdot v \cdot \omega \cdot \sin(\varphi)
 
where^{'} 

Note: the Coriolis effect increases the effective gravitationals acceleration slightly. It actually works horizontally (c_{H}) but, together with the gravitational acceleration, causes a slight deviation of the same and a minimal increase by c.
[3] Einfluss der Gravitation von Mond und Sonne
The influence of the tides is negligible in the calculations. The influence of the buoyancy of the atmosphere and the coriolis effect are very tiny and can be neglected too.
Reset resets all fields to their initial values. To reset only a specific field to its initial value, place the cursor in the field and press the ESC key. Clear sets all fields to 0.
GS: Speed of the aircraft with respect to the ground surface (ground speed).
Lat: Degree of Latitude of the aircraft position. The equator is 0, the North Pole 90 and the South Pole 90 degrees.
Lat_{cal}: Latitude at which the scale has been calibrated with the test mass W_{cal}.
W_{cal}: Weight of the test mass.
Course: heading in degrees North. North is 0, east is 90, south 180 and west is 270 degrees.
Alt: Altitude of the airplane above sea level.
Alt_{cal}: Altitude above sea level, on which the scale has been calibrated with the test mass W_{cal}.
Model: The earth is not a perfect sphere and can be approximated by an Ellipsoid. Model determines with which model the calculations are performed. For Sphere, the average radius R of the earth is used, see (2).
g_{rel}: Relative effective acceleration. This is the effective acceleration g_{h} in the aircraft relative to the effective acceleration g_{o} on the earth, see (23). If the aircraft is on the ground, g_{rel} = 1. Values less than 1 mean that due to the centrifugal acceleration, one is correspondingly lighter in the aircraft than on the ground.
W_{o}: Weight of the test mass displayed on the scale at the position of the aircraft at sea level.
g_{o}: Effective acceleration on the earth's surface, see (5). This corresponds to the vectorial sum of gravitational acceleration g_{oG} and centrifugal acceleration a_{oZ}.
g_{oG}: Gravitational acceleration on the earth's surface, see (9). Depending on the mass M of the earth and the distance R from the center of mass.
a_{oZ}: Centrifugal acceleration on the earth's surface, see (7). This is dependent on the rotational speed or rotation period T and the effective radius for the latitude Lat. The effective radius is the perpendicular distance of the point P from the earth axis. On the poles this radius is 0, on the equator it is equal to the radius of the earth at that location.
R: Radius of the earth at latitude Lat. This is the distance of the point P from the center of the earth, see (3). In the sphere model, this radius is the same size everywhere.
ρ_{1}: Radius of the red cutting ellipse at point P, i.e. the geodesic in east/west direction, see (41).
v_{eq}: Tangential velocity at the equator, v_{eq} = ω · R. Depends on the rotational speed ω or the rotational period T and the radius R on the equator, see (2).
g_{o,cal}: Effective gravitational acceleration at the point where the scale has been calibrated, ie at the latitude Lat_{cal} at altitude Alt_{cal}.
W_{h}: The weight of the test mass as displayed on the scale in the aircraft at the cruise altitude Alt.
g_{h}: Effective acceleration in the aircraft, see (11). This is the vectorial sum of gravitational acceleration g_{hG} and centrifugal acceleration a_{hZ} in the aircraft.
g_{hG}: Gravitational acceleration in the aircraft, see (17). Depending on the mass M of the earth and the distance from the mass center, i.e. the earth radius at latitude Lat and the altitude Alt.
a_{hZ}: Centrifugal acceleration in the aircraft, see (21). This is dependent on the tangential velocity v of the aircraft on the geodesic with respect to space in altitude Alt and the radius ρ_{h} of the geosdesic at the position of the aircraft.
ρ_{h}: Radius of the geodesic, see (25). In the sphere model, this is the radius R of the earth plus the altitude Alt of the aircraft. In the ellipsoid model, ρ_{h} is also dependent on the direction of flight Course and is a value between ρ_{1} and ρ_{2} plus the altitude Alt of the aircraft, see (24).
ρ_{2}: Radius of the blue cutting ellipse at point P, i.e. the geodesic in north/south direction, see (27).
v_{rot}: Tangential speed of the point P_{h} due to the earth's rotation, see (16). Is dependent on latitude Lat and the altitude Alt.
v: Combined speed of the aircraft and the rotation of the earth at latitude Lat, see (13). This is the tangential velocity of the aircraft on the geodesic with respect to a nonrotating earth. Together with the radius ρ_{h} of the geosdesic, this rate determines the centrifugal acceleration a_{hZ} acting in the aircraft.
The default values in the Calculation Form are from a real flight with a Bombardier Global Express. The aircraft had about 100 kt tailwind and flew at a speed of about 500 kt True Airspeed (TAS) east (kt or kn = knot = Nautical miles per hour). The velocity causing the centrifugal acceleration is composed of the tangential velocity due to the rotation of the earth v_{rot} at a latitude of −35° and the airspeed with respect to the earth surface of 600 kt (true airspeed TAS + tailwind), see (13).
Even under these extreme conditions, the centrifugal acceleration a_{hZ} is so small that the relative effective acceleration g_\mathrm{rel} barely shows a value below 1 on the Gdisplay: in particular 0,990 7796, which is rounded to 0,99.
This means that a man who has a weight of 100 kg on the ground at position P weighs only 99 kg in the aircraft.
Because the aircraft flies towards the east, that is, with the earth's rotation, the rotation and flight speed add up, resulting in a maximum centrifugal acceleration which makes the man lighter.
When the aircraft flies towards the west, i.e. contrary to the earth's rotation, the two speeds partly cancel out, and the man then weighs in the airplane roughly the same as on the ground. Check this by entering 270 at Course.
This effect is actually measurable: see Experiments with a Test Mass.
In the following sections, all the formulas used in the Calculation form are listed and explained:
The earth is not a perfect sphere. It is slightly flattened at the poles and the diameter at the equator is 42,8 km greater than at the poles. Gravitation on the surface is also not uniform, but varies by mass distribution on the surface and inside the earth.
For the calculations on this page I use a Reference ellipsoid. This is a rotation ellipse with the earth axis as the rotation axis and the origin at the center of the earth. This ellipsoid has the following parameters [1]:
(2) 
a = 6\,378\,137\ \mathrm{m} 
Semi major axes, i.e. radius on the equator  
b = 6\,356\,752{,}3142\ \mathrm{m} 
Semi minor axes, i.e. radius on the poles  
R = 6\,371\,008{,}8\ \mathrm{m} 
Average radius of the sphere earth  
g_\mathrm{e} = 9{,}780\,325\,3359\ \mathrm{m}/\mathrm{s}^{2} 
Effective acceleration on the equator  
g_\mathrm{p} = 9{,}832\,184\,9378\ \mathrm{m}/\mathrm{s}^{2} 
Effective acceleration on the poles  
G \, M = 3{,}986\,004\,418 \cdot 10^{14}\ \mathrm{m}^{3}/\mathrm{s}^{2} 
Geocentric gravitational constant [2]  
T = 86\,164{,}098\,903\,691\ \mathrm{s} 
Rotation period with respect to space (sidereal day) [3]  
\omega = 7{,}292\,115 \cdot 10^{−5}\ \mathrm{rad}/\mathrm{s} 
Angular speed  
where^{'} 

The product G·M can be determined more precisely than the individual factors [4].
In order to calculate the accelerations at a specific point P on the reference ellipsoid, we must calculate the position of the latitude of degree φ . Along the latitude through this position the accelerations are constant in magnitude.
The following formula can be used to calculate a point P on the surface of the earth with h = 0 or to compute a point P_{h} that is at a distance h from this point above the surface [5]. The connecting line of these two points is perpendicular to the ellipsoid.
(3) 
 
(4) 
 
with 
\epsilon = { \sqrt{ a^2  b^2 } \over a }
 
and 
N_\varphi = { a \over \sqrt{ 1  \epsilon^2 \cdot \sin( \varphi )^2 } }
 
where^{'} 

The origin of the coordinate system is at the center of the ellipsoid.
In geosciences, the effective (gravitational) acceleration of a celestial body is composed of its gravitational acceleration (gravitation) due to the mass of the body and the centrifugal acceleration in the reference system, which rotates with the body [6] [7].
The effective acceleration on the earth's surface g_\mathrm{o} is needed as a reference for the calculation of the relative effective acceleration g_\mathrm{rel} in the aircraft. The index o stands for the altitude 0, that is, the sea level.
The earth is slightly flattened on the poles due to its rotation. It has the form of a rotational ellipsoid. For such an ellipsoid, according to WGS84 the effective acceleration can be calculated as follows [1]:
(5) 
 
where^{'} 

The effective acceleration acts perpendicular to the surface of the ellipsoid at point P. It can be specified in vector form as follows:
(6) 

The centrifugal acceleration on the earth's surface a_{oZ} acts perpendicular to the rotation axis, depends on the degree of latitude φ and always acts outwards, i.e. its Z component is 0. The magnitude of the centrifugal acceleration is therefore equal to its X component.
(7) 
 
where^{'} 

The angular velocity ω indicates how fast the earth rotates about its axis. It can be calculated from the sidereal rotation period T as follows:
(8) 
\omega = { 2 \, \pi \over T }

The Sidereal day is the duration of a full revolution of the earth around itself against the fixed starry sky. The mean sidereal day on the earth is almost 4 minutes shorter than the sloar day of 24 houres, see T in (2).
The gravitational acceleration at point P can be determined vectorially:
(9) 
 
(10) 
 
where^{'} 

Airplanes fly the shortest possible connection between two points on the earth's surface. Such a connection line is the Geodesic. On a sphere, each geodesic is located on a Great circle.
If the earth is approximated by an Ellipsoid, geodesics generally do not form closed curves, see picture. To simplify the calculations on this page, I approximate the geodesics by a cutting ellipse optained by an intersection plane through the ellipsoid. These ellipses pass through the point P and contain the perpendicular through the point P. These ellipses are rotated by a certain angle α from the longitude through P. For these ellipses the radius of curvature ρ relevant to the centrifugal acceleration can then be calculated at point P.
The effective acceleration in the aircraft is composed of gravitational and centrifugal acceleration. Please note the following:
The centrifugal acceleration in the aircraft does not act perpendicular to the axis of rotation of the earth but upwards perpendicular from the surface of the ellipsoid because the aircraft moves on a geodesic (blue) with respect to a nonrotating ellipsoid. This has a different curvature ρ than the longitude or latitude of the ellipsoid at the point P and the center of the osculating circle of the geodesic lies not on the axis of rotation of the earth but on the violet axis with angle φ in the image.
The Inertial Reference System measures the accelerations in 3 mutually independent orthogonal axes. The Z direction points upwards in respect to the aircraft. In cruise, all forces on the aircraft are balanced so that the effective acceleration acts along the negative direction of the Z axis.
The effective acceleration is obtained by vectorial addition of the gravitational and centrifugal acceleration:
(11) 
 
(12) 
 
where^{'} 

In order to calculate the accelerations in the aircraft, we must calculate its position P_{h} from the latitude φ and the altitude h over sea level.
The position P_{h} of the aircraft can be calculated by the formula (3).
To calculate the centrifugal acceleration a_{hZ} in the aircraft, we need its absolute velocity (speed) v on the geodesic. This is the speed with respect to a nonrotating ellipsoid. It is vectorially composed of the tangential velocity v_{rot} of the point P_{h} due to the earth's rotation and the velocity v_{gs} and the course α of the aircraft with respect to the surface (ground speed GS).
For the calculations, a flat 2dimensional coordinate system is used at the points P and P_{h}, respectively, with the Y coordinate facing north and the X coordinate facing east.
(13) 
 
(14) 
 
where^{'} 

The speed v_{rel} at altitude is somewhat higher than the ground speed v_{gs} because of the earth curvature.
(15) 
 
where^{'} 

The tangential velocity of the point P_{h} has only a component in the X direction and is dependent on the degree of latitude φ :
(16) 
 
where^{'} 

The trajectory of the aircraft is a geodesic which is located on an extended ellipsoid which has the local perpendicular distance h to the ellipsoid of the earth's surface. The position P_{h} is calculated using formula (3), by using Alt for the altitude h.
To calculate the effective acceleration at the point P_{h} at a distance h from the reference ellipsoid, there is a formula according to WGS84. The corresponding acceleration acts perpendicular to the surface of the ellipsoid and is composed of gravitational acceleration and centrifugal acceleration due to earths rotation.
However, the aircraft is not connected to the surface and is therefore not exposed to the centrifugal acceleration of the surface. The Centrifugal acceleration in the aircraft must be determined in a different way.
The gravitational acceleration g_\mathrm{hG} in the aircraft is obtained by subtracting the centrifugal acceleration a_\mathrm{ohZ} due to earths rotation from the effective acceleration g_\mathrm{oh} at altitude h calculated according to WGS84.
(17) 
 
where^{'} 

The effective acceleration according to WGS84 for the altitude h can be calculated as follows [1]:
(18) 
 
with 
f = { a  b \over a }
 
and 
m = { { \omega }^2 \cdot { a }^2 \cdot b \over G \, M }
 
where^{'} 

The effective acceleration according to WGS84 acts perpendicular to the surface of the ellipsoid. The vector representation is therefore:
(19) 
\vec g_\mathrm{oh} =  g_\mathrm{oh} \cdot \pmatrix{ \cos( \varphi ) \\ \sin( \varphi ) }

The centrifugal acceleration due to the rotation of the earth at point P_{h} is:
(20) 
 
where^{'} 

In contrast to the centrifugal acceleration of the earth's surface, the centrifugal acceleration in the aircraft acts away from the geodesic curvature, i.e. perpendicular to the surface of the ellipsoid at the point P_{h}. Its magnitude can be calculated from the absolute velocity of the aircraft v on its nonrotating trajectory (geodesic) and the radius of curvature ρ_{h} of the geodesic at altitude h.
(21) 
 
where^{'} 

The angle \theta of the geodesic with respect to the nonrotating ellipsoid can be calculated from the total velocity \vec v, see (13). This velocity takes the direction of flight α and the rotation of the earth into account. Note that \vec v does not have the same heading as the Ground Speed \vec v_\mathrm{gs} because of the rotation of the Earth.
(22) 
 
where^{'} 

If v = 0 then \theta = 0 can be set because the centrifugal acceleration in the aircraft is in this case 0 anyway.
On the Gdisplay, the Zcomponent of the effective acceleration in the aircraft is displayed with respect to the effective acceleration g_\mathrm{o} of the earth's surface under the aircraft:
(23) 
 
where^{'} 

If the aircraft is on the ground, g_\mathrm{o} and g_\mathrm{h} are equal, so g_\mathrm{rel} = 1{,}00 is displayed.
Notice: May be the aircraft uses a mean effective acceleration of g_{o} = 9,806 65 m/s^{2} instead of the above computed real effective acceleration at the point P.
In order to be able to calculate the centrifugal acceleration a_{hZ} (21) in the aircraft on its trajectory around the earth, we need the radius of curvature ρ_{h} of the trajectory at point P_{h}. We obtain the radius of curvature by calculating the radius of curvature ρ of the geodesic on the earth ellipsoid and adding h.
The calculation of ρ takes place via the green hatched cutting ellipse. The rotation axis of the green cutting ellipse is the connecting line PQ and is rotated by the angle γ with respect to north direction. This rotation axis is in general not identical with the major axis of the ellipse!
I could not find any formulas for calculating the parameters of the green cutting ellipse. However, I can estimate the radius of curvature ρ (perhaps the formula shown here is even correct) by calculating the maximum radius of curvature ρ_{1} of the red cutting ellipse and the minimum radius of curvature ρ_{2} of the blue cutting ellipse and then interpolating the angle γ with a cosine function. The radius ρ depends on γ and has a value between the minimum and maximum radius:
(24) 
 
(25) 
 
where^{'} 

Note that in the conversion of the ground speed to the speed at altitude (15) the geodesic in the coordinate system rotating with the earth must be used. These geodesic correspond to the cutting ellipse rotated by the angle γ = α, where α is the heading (azimuth) with respect to the rotating earth.
For the centrifugal acceleration a_{hZ}, the geodesic must be described in the nonrotating coordinate system since the aircraft is detached from the earth. The rotation angle γ for the corresponding cutting ellipse can be calculated using the absolute velocity \vec v, see (22).
For the calculation of the radii of curvature ρ_{1} and ρ_{2}, I need the lengths of the semi major axes of the red and blue ellipse.
The blue ellipse is the northsouth section through the ellipsoid. The two semi axes correspond to the maximum and minimum radius of the earth:
(26) 
a_\mathrm{S} = a \qquad b_\mathrm{S} = b

The smaller radius of curvature ρ_{2} at the point P can be calculated with the data of the blue ellipse (see figure under Calculating the curvature radius of the geodesic), [8]:
(27) 
 
where^{'} 

In order to obtain the radii of the red cutting ellipse (see figure under Calculating the curvature radius of the geodesic), we must calculate the intersection point Q of the straight line PQ with the blue cutting ellipse. For this, we introduce the equations for the ellipse and the line:
(28) 
{ { x }^2 \over { a }^2 } + { { z }^2 \over { b }^2 }  1 = 0

Ellispe equation 
(29) 
x = P_\mathrm{x} + \lambda \cdot s_\mathrm{x} \qquad z = P_\mathrm{z} + \lambda \cdot s_\mathrm{z}

Line equation 
with 
s_\mathrm{x} = \cos( \varphi ) \qquad s_\mathrm{z} = \sin( \varphi )

The intersections of the ellipse with the straight line are obtained by inserting the straight line equation in the ellipse equation.
(30) 
{ { \left( P_\mathrm{x} + \lambda \cdot s_\mathrm{x} \right) }^2 \over { a }^2 } + { { \left( P_\mathrm{z} + \lambda \cdot s_\mathrm{z} \right) }^2 \over { b }^2 }  1 = 0

Multiplying and sorting the terms after λ yields a quadratic equation for λ:
(31) 
\left( { { s_\mathrm{x} }^2 \over { a }^2 } + { { s_\mathrm{z} }^2 \over { b }^2 } \right) \cdot { \lambda }^2 + \left( { 2 \cdot P_\mathrm{x} \cdot s_\mathrm{x} \over { a }^2 } + { 2 \cdot P_\mathrm{z} \cdot s_\mathrm{z} \over { b }^2 } \right) \cdot \lambda + \left( { { P_\mathrm{x} }^2 \over { a }^2 } + { { P_\mathrm{z} }^2 \over { b }^2 }  1 \right) = 0

One of the two solutions is already known: it is the point P at which λ = 0. Substituting λ = 0 into (31) yields:
(32) 
\lambda = 0 \qquad \Rightarrow \qquad { { P_\mathrm{x} }^2 \over { a }^2 } + { { P_\mathrm{z} }^2 \over { b }^2 }  1 = 0

Since P lies on the ellipse, this equation is true. Because the last term is 0, it drops from equation (31). We can divide the remaining equation on both sides by λ because λ for the point Q is not zero. Thus we obtain a linear equation for λ:
(33) 
\color{blue}{ \left( { { s_\mathrm{x} }^2 \over { a }^2 } + { { s_\mathrm{z} }^2 \over { b }^2 } \right) } \cdot \lambda + \color{green}{ \left( { 2 \cdot P_\mathrm{x} \cdot s_\mathrm{x} \over { a }^2 } + { 2 \cdot P_\mathrm{z} \cdot s_\mathrm{z} \over { b }^2 } \right) } = \color{blue}{ A } \cdot \lambda + \color{green}{ B } = 0

Now we can simply solve for λ:
(34) 
 
with 
A = \color{blue}{ \left( { { s_\mathrm{x} }^2 \over { a }^2 } + { { s_\mathrm{z} }^2 \over { b }^2 } \right) } \qquad B = \color{green}{ \left( { 2 \cdot P_\mathrm{x} \cdot s_\mathrm{x} \over { a }^2 } + { 2 \cdot P_\mathrm{z} \cdot s_\mathrm{z} \over { b }^2 } \right) }
 
where^{'} 

If we insert this λ into the line equation (29), the point Q = (x, z) is obtained:
(35) 
Q_\mathrm{x} = P_\mathrm{x} + \lambda \cdot s_\mathrm{x} \qquad Q_\mathrm{z} = P_\mathrm{z} + \lambda \cdot s_\mathrm{z}

In (29) we have chosen \vec s = (s_\mathrm{x}, s_\mathrm{z}) so that its length is 1. Therefore, the absolute value of λ is just the distance of the two points P and Q. The semi minor axis now is half of this distance:
(36) 
 
where^{'} 

For further calculations, we need the coordinates of the center O of the red ellipse:
(37) 
O_\mathrm{x} = P_\mathrm{x} + { \lambda \over 2 } \cdot s_\mathrm{x} \qquad O_\mathrm{z} = P_\mathrm{z} + { \lambda \over 2 } \cdot s_\mathrm{z}

For the calculation of the semi major axis a_{S} of the red ellipse, I use the following trick: If the ellipsoid together with the red ellipse is stretched in the Z direction so that the ellipsoid becomes a sphere with radius a and the red ellipse becomes the red dotted circle, the geometry in width does not change. The semi major axis a_{S} of the red ellipse is therefore equal on the ellipsoid as on the sphere. The semi major axis on the sphere can easily be calculated.
To obtain a sphere, all coordinates in the Z direction must be multiplied by the factor a / b. The semi major axis a_{S} of the red ellipse passes through the point O. Therefore, we must extend the coordinates of O accordingly:
(38) 
O^{\,\prime} = \pmatrix{ O_\mathrm{x}^{\,\prime} \\ O_\mathrm{z}^{\,\prime} } = \pmatrix{ O_\mathrm{x} \\ (a/b) \cdot O_\mathrm{z} }

Next, we need the distance m between O^{\,\prime} and the center M = (0,0) of the sphere:
(39) 
m = \sqrt{ { O_\mathrm{x}^{\,\prime} }^2 + { O_\mathrm{z}^{\,\prime} }^2 }

We now obtain the semi major axes of the red ellipse via Pythagoras:
(40) 
 
where^{'} 

The desired radius of curvature of the red ellipse (see figure under Calculating the curvature radius of the geodesic) lies at the vertex of the semi minor axis and can therefore be calculated as follows [8]:
(41) 
 
where^{'} 
