User:Romeowint

The universal minimum speed formula

This page is meant to reveal the study of the International Grassroots Space Organization of North America (IGSONA). The study of IGSONA defines flying by means of a simple formula, which is the universal formula of all flying objects around an astronomical body --Romeowint (talk) 16:36, 14 February 2010 (UTC). This formula indicates the minimum speed which a mass must possess in order to fly around an other astronomical mass.

What is this speed?

Einstein stated that ${\displaystyle E=mc^{2}}$

and it is derived that

${\displaystyle E\approx m_{0}c^{2}+{\frac {1}{2}}m_{0}v^{2}}$

${\displaystyle m_{0}c^{2}}$ is the energy of the rest mass.

${\displaystyle {\frac {1}{2}}m_{0}v^{2}}$ is the Newton kinetic energy of the mass mentioned above.

This study is focused on the speed "${\displaystyle v}$" of the Newton kinetic energy.

The minimum circular speed formula helps us to described most phenomena between an altitude of 10 km and 120 km above the Earth surface.

The study of IGSONA indicates that a flight from New York to Beijing, for example, will last less than two hours. The study also indicates that the new generation of manned winged spacecraft will not required heat shield upon returning into the Earth atmosphere.

The formula tells us the speed of everything from a mosquito through the speed of the Earth Moon.

Facts	Earth Radius [m]	Altitude [m]	ρ [kg/m^3]	g [m/s^2]	${\displaystyle S_{ref}}$ [m^2]	${\displaystyle C_{L}}$ [ ]	r [m]	m [kg]	${\displaystyle M_{E}}$ [kg]	G [m^3/kg^2]	v [m/s]	v [km/h]	v [mph]
Artificial Earth Moon	6378160	411478160	0	0.002283397		1	417856320	770	5.97E+24	6.67E-11	976.79	3516.46	2183.73
Moon	6378160	378368840	0	0.002693287		1	384748000	7.48E+22	5.97E+24	6.67E-11	1017.96	3664.65	2275.74
Geo Stationary Orbit	6378160	35786000	0	0.224258261		1	42164160	490	5.97E+24	6.67E-11	3075.01	11070.02	6874.48
GPS Satellites	6378160	20183000	0	0.565120783		1	26561160	770	5.97E+24	6.67E-11	3874.31	13947.51	8661.40
Hubble Space Telescope	6378160	569000	1.56E-31	8.260774223		1	6947160	11110	5.97E+24	6.67E-11	7575.55	27271.97	16935.89
Int Space Station	6378160	330000	1.47E-18	8.859894074		1	6708160	300214	5.97E+24	6.67E-11	7709.31	27753.55	17234.95
Shenzhou Space Vehicle	6378160	200000	1.68E-11	9.21353824	4.54	1	6578160	7840	5.97E+24	6.67E-11	7785.12	28026.44	17404.42
Any reentry Space Vehicle	6378160	120000	3.70E-07	9.441794721	95	1	6498160	17300	5.97E+24	6.67E-11	7807.16	28105.78	17453.69
Ideal Space Vehicle	6378160	80000	5.49E-05	9.559116492	95	1	6458160	16818	5.97E+24	6.67E-11	5553.04	19990.95	12414.38
Andea Male Condor in Nature	6378160	145	1.188	9.79997098	1.13	0.7	6378305	11.7	5.97E+24	6.67E-11	15.62	56.23	34.92
Concorde	6378160	5	1.209	9.800401202	358.22	1	6378165	185065	5.97E+24	6.67E-11	91.50	329.41	204.57
TU-44	6378160	5	1.209	9.800401202	438	1	6378165	180000	5.97E+24	6.67E-11	81.61	293.80	182.45
Space Shuttle	6378160	5	1.209	9.800401202	396	1	6378165	100000	5.97E+24	6.67E-11	63.97	230.31	143.02
Space Ship One	6378160	5	1.209	9.800401202	15	1	6378165	1801	5.97E+24	6.67E-11	44.11	158.81	98.62
Shenzhou Capsule	6378160	5	1.209	9.800401202	4.54	1	6378165	3840	5.97E+24	6.67E-11	117.07	421.48	261.74
Soyuz Capsule	6378160	5	1.209	9.800401202	3.7	1	6378165	3600	5.97E+24	6.67E-11	125.57	452.04	280.71
A320 Airbus	6378160	5	1.209	9.800401202	245.2	1	6378165	77000	5.97E+24	6.67E-11	71.34	256.63	159.11
Boeing 737-300	6378160	5	1.209	9.800401202	249.6	1	6378165	78015	5.97E+24	6.67E-11	71.17	256.23	159.12
BMW 528i Max Ground Sp	6378160	5	1.209	9.800401202	8.5	1	6378165	1715	5.97E+24	6.67E-11	57.19	205.87	127.85

${\displaystyle V={\sqrt {\frac {r*g}{[{\frac {r}{2m}}(R*S_{ref}*C_{L})+1]}}}\,\!}$ --Romeowint (talk) 15:53, 14 February 2010 (UTC) OR

${\displaystyle V={\sqrt {\frac {\frac {G*M_{E}}{r}}{[{\frac {r}{2m}}(R*S_{ref}*C_{L})+1]}}}\,\!}$ --Romeowint (talk) 15:53, 14 February 2010 (UTC)

Where:

- V is the minimum circular speed of the object that keep it flying

- r is the distance from the center of the earth through the center of the object

- g is the gravity between earth and the object at the distance r

- R or 0 ≤ (ρ) ≤ 1.21 is the density of the surrounding air of the object at the distance r

- ${\displaystyle S_{ref}}$ is the reference area that carries the object

- ${\displaystyle C_{L}}$ is the lift coefficient of the object and ${\displaystyle C_{L}}$ ≥ 0

- m is the mass of the object at the distance r

- ${\displaystyle M_{E}}$ is the mass of the Earth

- G is the gravitational constant