<p> TableIII Piot Data</p>

3d42f296-6dd1-41a8-9507-b948bc1a7ea5 57 4 5 decimal

&[DATE] &[TIME] - &[FILENAME]

OACI cockpit altitude(m) vs kPa ...

OACI uncorrected altitude[m] vs  kPa x OACI 576300140 x * 4053 / ln 5.255 / exp - (* 13 / :

x λ 1 1.2 x ≤ (x 113.93 ≤ (& cases :

OACI down to -1000 m ... up to 25000 m

x OACI x λ * 101.325 15000 101.325 5000 - ( 2 2 mat 53 12000 101.325 kPa 12 black 1 5 mat 3 1 sys

1.2 OACI 25272

22.272 OACI 11103

x OACI 1000 + x 110115 solve 113.93

x OACI 1000 + x 90 roots 113.93

This formula DOES NOT correct cockpit altitude vs local or actual °C. Strickly technical. Interesting single fit ... as accurate as any pretention. Compatible 'roots'

When the temperature is warmer than standard, your altimeter will indicate you are lower than you actually are. This means you are at a higher altitude than your altimeter shows

The inverse is more dangerous, when it is colder than standard your altimeter will erroneously indicate you are higher than you actually are, possibly putting you dangerously close to obstacles or terrain.

OACI corrected flying altitude(m) vs °C ...

p[kPa] from altimeter

p OACI 576300140 p * 4053 / ln 5.255 / exp - (* 13 / : p t Flight p OACI p OACI t C + : 31 sys

raw altimeter reading

... flight altitude [m]

't' °C from the airport "OR" as measured at aircraft approaching landing runway.

Altimeter kPa from sensed

laps 0.0065 : (standard ISA temperature laps rate °C/m ≡ H 0 : (sea level elevation [m] ≡ m 1 : (meter unit ≡ h OACI(kPa)altimeter reading ≡ 41 sys

Local °C flight altitude correction
add [m] to  altimeter reading [h] h t C h 15 t laps H * + (- 273 t laps H * + (+ 0.5 laps * h H + (* - / * :

x c 1 22.272 x ≤ (x 101.325 ≤ (& cases :

x correct 10 x ≤ (x 1500 ≤ (& cases :

x 15 Flight x c * x 50 - Flight x c * x 50 Flight x c * 101.325 0 + 50 red 1 5 mat 4 1 sys x 30 - C x correct * x 50 C x correct * 2 1 sys

add[m]Alt reading

t 15 °C * <

150050 - C 150015 C 150050 C 31 mat m * 447 m * 0165 m * - 31 mat

t 15 °C * >

subtract[m]Alt reading

flying high danger flying low safe 21 sys

subtract from altitude reading. x 50 - Flight 4096 - x 6480 solve m * 69 m *

OACI ... December 7 1944 ISA .... April 28 1945 NASA ... July 29 1958

g 9.80665 : R 287.052874 : po 1013.25 : p1 226.321 : z1 11000 : To 288.15 : T1 216.65 : λ 0.0065 - : 81 sys

z ISA0 po To λ z * + To / (g - R λ * /^* : z ISA11 p1 g z z1 - (* R T1 * / - exp * : 21 sys

The two ISA segments

x c0 10 x ≤ (x 11000 ≤ (& cases : x c11 111000 x ≤ (x 25000 ≤ (& cases : 21 sys

x ISA0 x c0 * x ISA11 x c11 * 11000 600 11000 200 - 2 2 mat 5000 768 Troposphere 12 blue 1 5 mat 14000 256 Tropopause 12 red 1 5 mat 5 1 sys

ISA altitude[kPa] ... maple_solve hPa alt0 To 1 - 10 hPa * po / ln R * λ * g / - exp + (* λ / : hPa alt11 g z1 * - 10 hPa * p1 / ln R * T1 * + g / - : 21 sys

lowest local barometric 
ISA reference
highest local barometric 87 alt0 101.325 alt0 108.38 alt0 31 mat 12670571 - 31 mat

x alt0 x alt11 101.325 0 + 40 black 1 5 mat 22.63204 10105 + 40 black 1 5 mat 4 1 sys

u 22.632039834 :

u alt11 u alt0 - 0.016653207

u ISA0 10 * 10105

u ISA11 10 * 12779

22.63204 is the closest kPa of tangency between the two ISA segments.

x alt11 25000 - x 1 roots 2.4886

x alt11 11000 - x 5 roots 22.6321

x alt0 11000 - x 5 roots 22.632

2.4886 alt0 22.632 alt0 22.632 alt11 22.632 OACI 2.4886 OACI 51 mat 224321100011000110022243451 mat

x alt0 x alt11 - 22.6321 0.016653 - + 100 red 1 5 mat 2 1 sys

You can fly safely well above ... ▲ 11000 m tropopause either OACI/ISA/NASA/Thiele

More interesting stuff . . .

]]>

NASA Atmospheric kPa(m)... as published h NASA 101.29 288.14 0.00649 h * - 288.08 / (5.256^* 1000 - h ≤ (h 11000 ≤ (& 22.65 1.73 0.000157 h * - exp * 11000 h ≤ (h 25000 ≤ (& 2.488 141.89 0.00299 h * + 216.6 / (11.388 -^* cases :

0 NASA 11000 NASA 25000 NASA 60000 NASA 41 mat 101.4009 22.7074 2.5223 0.0279 41 mat

101.4009 22.7074 2.5223 31 mat OACI vectorize m * 6 m * - 10981 m * 22378 m * 31 mat

25000 NASA 2.5223

NASA Altitude  m(kPa)... from Smath/Maple companions. kPa alt 20001440714404100 kPa * 10129 / ln 5.256 / exp * - (* 649 / 101.400931 kPa ≥ (kPa 22.7074 ≥ (& 1000017310020 kPa * 453 / ln * - (* 157 / 22.7074 kPa ≥ (kPa 2.5223 ≥ (& 100014189 - 21660125 kPa * 311 / ln 11.388 / - exp * + (* 299 / cases :

header kPa NASA ISA OACI 14 mat :

22.6315 OACI 22.7074 OACI 12.9182 OACI 5 OACI 50 OACI 51 mat 11002109811437519325557551 mat

NASA 22.6315 alt 22.7074 alt 12.9182 alt 5 alt 50 alt 51 mat 11024110001459620642558851 mat

ISA 22.6315 alt0 22.7074 alt11 12.9182 alt11 5 alt11 50 alt0 51 mat 11000109791455620575557451 mat

Triplet header 22.6315 22.7074 12.9182 55051 mat 11024110001459620642558851 mat 11000109791455620575557451 mat 11002109811437519325557551 mat augment stack :

Comparative triplet
@ some cockpit kPa . Triplet kPa NASA ISA OACI 22.6315 110241100011002 22.7074 110001097910981 12.9182 14596145561437552064220575193255055885574557564 mat

x c 1 2.5223 x ≤ (x 101.401 ≤ (& cases :

Global NASA ... up to 25000 m

x alt x c * 0 18300 7.235 18300 2 2 mat 0 11000 22.707 11000 2 2 mat 16 20000 Global 7000 12 red 1 5 mat 32 13000 A 320 12 green 1 5 mat 2.522 25000 + 20 black 1 5 mat 6 1 sys

101.325 alt 6.3272

101.400931 alt 0.000008 -

0 NASA 101.400931

x alt x c * 018300 7.235 1830022 mat 011000 22.707 1100022 mat 1620000 Global 7000 12 red 15 mat 3213000 A 320 12 green 15 mat 2.522 25000 + 20 black 15 mat 61 sys

..... -10,210 is in error .....

FAR 43 - Appendix E [Altimeter] Tol alt[ft] inchHg ±ft 1000 - 31.018 200 29.921 20500 29.385 201000 28.856 201500 28.335 252000 27.821 303000 26.817 304000 25.842 356000 23.978 408000 22.225 6010000 20.577 8012000 19.029 9014000 17.577 10016000 16.216 11018000 14.942 12020000 13.750 13022000 12.636 14025000 11.104 15530000 8.885 18035000 7.041 20540000 5.538 23045000 4.355 25550000 3.425 280243 mat :

http://www.faa-aircraft-certification.com/43-appendix-e.html

Tol Tol 224 range 13 range el : X Tol 1 col : Y Tol 3 col : 12 mat 31 sys

x y axes x y / - :

visible ErrorBar ν 10 :

N i 1 Tol rows range E i el ν Y * (i el : Nest i el X i el X i el E i el + X i el X i el E i el - 22 mat : 21 line for Nest 21 line :

Lab i 1 Tol rows range E i el Y i el : read i el X i el X i el E i el + X i el E i el - 21 mat 12 mat : 21 line for read 21 line :

Tabulate "Lab" to see suggested Lab Document to be filled-in for certification as per regulation FAR 43.

j 1 N rows range Ω j el N j el 1 col N j el 2 col augment : for

Test X X augment :

50000 ft * 280 ft * ± 12 mat 15240 m * 85.34 m * 85.34 m * - 21 sys 12 mat

35000 ft * 205 ft * ± 12 mat 10668 m * 62.48 m * 62.48 m * - 21 sys 12 mat

Test Ω axes 3 1 sys

'Ω' explorer. j 20 :

OACI/ISA/NASA seat within TOL  Altimeter calibration Triplet 314 range el 22.7074 11000109791098114 mat

Ω j el ft * 10668 m * 11292.84 m * 10668 m * 10043.16 m * 22 mat

Q i 1 Tol rows range E i el 1 Y * (i el : Nest i el X i el E i el X i el E i el - 22 mat : 21 line for Nest 21 line :

j 1 Q rows range TOL j el Q j el 1 col Q j el 2 col augment : for

TOL axes 2 1 sys

Ω 11 mat 1000 - 800 - 1000 - 1200 - 22 mat 02000200 - 22 mat 50070050030022 mat 10001200100080022 mat 150017501500125022 mat 200023002000170022 mat 300033003000270022 mat 400043504000365022 mat 600064006000560022 mat 800086008000740022 mat 100001080010000920022 mat 1200012900120001110022 mat 1400015000140001300022 mat 1600017100160001490022 mat 1800019200180001680022 mat 2000021300200001870022 mat 2200023400220002060022 mat 2500026550250002345022 mat 3000031800300002820022 mat 3500037050350003295022 mat 4000042300400003770022 mat 4500047550450004245022 mat 5000052800500004720022 mat 231 mat 11 mat

TOL 11 mat 1000 - 201000 - 20 - 22 mat 020020 - 22 mat 5002050020 - 22 mat 100020100020 - 22 mat 150025150025 - 22 mat 200030200030 - 22 mat 300030300030 - 22 mat 400035400035 - 22 mat 600040600040 - 22 mat 800060800060 - 22 mat 10000801000080 - 22 mat 12000901200090 - 22 mat 1400010014000100 - 22 mat 1600011016000110 - 22 mat 1800012018000120 - 22 mat 2000013020000130 - 22 mat 2200014022000140 - 22 mat 2500015525000155 - 22 mat 3000018030000180 - 22 mat 3500020535000205 - 22 mat 4000023040000230 - 22 mat 4500025545000255 - 22 mat 5000028050000280 - 22 mat 231 mat 11 mat

READ MORE:https://www.skybrary.aero/solutions/levelbust/BNotes/BN_Ops2.pdf

. . . Thiele [0 . . 25 km] . . .

]]>

g 9.806645 : R 287.0528 : po 101.325 : p1 22.6321 : z1 11000 : To 288.15 : T1 216.65 : λ 0.0065 - : 81 sys

ISA altitude[kPa] ... maple_solve kPa alt11 To 1 - kPa po / ln R * λ * g / - exp + (* λ / : kPa alt25 g z1 * - kPa p1 / ln R * T1 * + g / - : 21 sys

x kPa25 1 2.489 x ≤ (x 22.632 ≤ (& cases : x kPa11 1 22.632 x ≤ (x 101.325 ≤ (& cases : 21 sys

altitude x alt25 x kPa25 * x alt11 x kPa11 * 22.632 16000 22.632 4000 - 22 mat 820000 Troposphere 12 blue 15 mat 488000 Tropopause 12 red 15 mat 101.325 0 + 40 black 15 mat 22.632 11000 + 50 black 15 mat 3213000 commercial 12 black 15 mat 81 sys :

ISA 1976 atmospheric altitude [m] vs kPa

altitude

L H N xd U 0 : dx H L - N 1 - / : 12 mat i 1 N range U i el L dx - (dx i * + eval : for U 31 line :

L 2.489 : H 22.632 : N 10 : 13 mat u L H N xd : 21 line

L 22.632 : H 101.325 : N 20 : 13 mat v L H N xd : 21 line

XY11 i 1 u rows range y i el u i el alt25 eval : for u y 1 round vectorize augment 21 line :

XY25 i 1 v rows range y i el v i el alt11 eval : for v y 1 round vectorize augment 21 line :

data char size clr plot k 1 data rows range r3 k el char : r4 k el size : r5 k el clr : 13 mat for data r3 r4 r5 augment 21 line :

data XY11 XY25 stack :

data rows 30

data 2.489 24999 4.7271 20931.3 6.9652 18473.2 9.2033 16706.2 11.4414 15325.8 13.6796 14192.8 15.9177 13231.9 18.1558 12397.6 20.3939 11660.4 22.632 11000 22.632 11000 26.7737 9917 30.9155 8962.3 35.0572 8106 39.1989 7328.1 43.3407 6614.2 47.4824 5953.5 51.6242 5338 55.7659 4761.2 59.9076 4218.2 64.0494 3704.7 68.1911 3217.5 72.3328 2753.7 76.4746 2310.9 80.6163 1887.1 84.7581 1480.5 88.8998 1089.8 93.0415 713.6 97.1833 350.6 101.325 0302 mat :

M r DelRow N 0 : ct 1 : n 1 M rows range n r ≠ N ct 1 el M n row : ct ct 1 + : 21 line Unest 'N' if for v N 1 el : j 2 N rows range v v N j el stack : for v 61 line :

data data 11 DelRow :

data data eval :

β 24.06 - 8659.028 - 95.972 9.579 14.887 50.785 - 4.371 - 2.1492 106^* 401.742 3.314 1002.12 84.929 121 mat :

X data 1 col : Y data 2 col : 12 mat

data data o 5 black plot :

data char size clr plot k 1 data rows range r3 k el char : r4 k el size : r5 k el clr : 13 mat for data r3 r4 r5 augment 21 line :

x c 1 2.489 x ≤ (x 101.325 ≤ (& cases :

x f β 1 el x * β 2 el + β 8 el x β 3 el + β 9 el x β 4 el + β 10 el x β 5 el + β 11 el x β 6 el + β 12 el x β 7 el + / + / + / - / - / + :

header kPa alt[m] Δ[m] 13 mat :

N X Y Y X f 0 round - vectorize augment :

N header N stack :

sanity datum ISA 101.325 f 0.104

Thiele 12 from GenfitMatrix 6/5 [0 ... 25 km] ... ± 1 m

data x f x c * 22.632 11000 + 50 blue 1 5 mat 101.325 0 + 50 blue 1 5 mat 4 1 sys

N 11 mat kPa alt[m] Δ[m] 2.489 249992 - 4.727 20931.3 0.7 - 6.965 18473.2 0.2 9.203 16706.2 0.2 11.441 15325.8 0.2 - 13.68 14192.8 0.2 - 15.918 13231.9 0.1 - 18.156 12397.6 0.4 - 20.394 11660.4 0.6 - 22.632 110000 26.774 99170 30.916 8962.3 0.7 - 35.057 81060 39.199 7328.1 0.1 43.341 6614.2 0.2 47.482 5953.5 0.5 51.624 53380 55.766 4761.2 0.2 59.908 4218.2 0.2 64.049 3704.7 0.3 - 68.191 3217.5 0.5 - 72.333 2753.7 0.3 - 76.475 2310.9 0.1 - 80.616 1887.1 0.1 84.758 1480.5 0.5 - 88.9 1089.8 0.2 - 93.042 713.6 0.4 - 97.183 350.6 0.4 - 101.325 00303 mat 11 mat

http://www.pdas.com/atmosTable2SI.html

The standard air pressure at sea level is 14.7 pounds per square inch, or about 100 kilopascals. Air pressure is so minimal at the top of the thermosphere that an air molecule can travel large distances before hitting another air molecule.

Troposphere The troposphere starts at the Earth's surface and extends 8 to 14.5 kilometers high (5 to 9 miles). This part of the atmosphere is the most dense. Almost all weather is in this region. Stratosphere The stratosphere starts just above the troposphere and extends to 50 kilometers (31 miles) high. The ozone layer, which absorbs and scatters the solar ultraviolet radiation, is in this layer. Mesosphere The mesosphere starts just above the stratosphere and extends to 85 kilometers (53 miles) high. Meteors burn up in this layer Thermosphere The thermosphere starts just above the mesosphere and extends to 600 kilometers (372 miles) high. Aurora and satellites occur in this layer. Ionosphere The ionosphere is an abundant layer of electrons and ionized atoms and molecules that stretches from about 48 kilometers (30 miles) above the surface to the edge of space at about 965 km (600 mi), overlapping into the mesosphere and thermosphere. This dynamic region grows and shrinks based on solar conditions and divides further into the sub-regions: D, E and F; based on what wavelength of solar radiation is absorbed. The ionosphere is a critical link in the chain of Sun-Earth interactions. This region is what makes radio communications possible. Exosphere This is the upper limit of our atmosphere. It extends from the top of the thermosphere up to 10,000 km (6,200 mi)

vx vy char size color plotG n vx length : plot vx 1 el vy 1 el char size color augment : i 2 n range plot plot vx i el vy i el char size color augment stack : for plot 41 line :

km.. ρ...hPa......°C 11 mat

ISA 00101315 0.5 0955 11.8 10900 8.5 1.5 0845 5.3 207942 2.5 0746 1.3 - 30700 4.5 - 3.5 0658 7.8 - 4061711 - 50541 17.5 - 6047124 - 70411 30.5 - 8035737 - 90307 43.5 - 10026550 - 110227 56.5 - 120194 56.5 - 130165 56.5 - 140141 56.5 - 150121 56.5 - 2005546 - 3001138 - 40035 - 500 0.9 1600 0.25 20 - 1000 0.0004 64 - 2000 0.0000013 52.2 - 3000 0.0000002 95.3 - 4000 0.000000044 97.3 - 5000 0.000000011 97.7 - 304 mat :

P ISA 1 col ISA 3 col 0.1 * . 10 black plotG : T ISA 1 col ISA 4 col . 10 blue plotG : °C ISA 1 col ISA 4 col augment : 31 line

P T °C 56.5 - 3 1 sys T °C 56.5 - 3 1 sys

Rescue altitude reading ... NOT °C corrected

Thiele ,,, 'x' is static  kPa ... Plug in your calculator, compatible continued frsction. x Thiele 120350 / - (x * 2164757250 / - + 2149200 x 23993250 / + 200871500 / x 95791000 / + 1657500 / x 148871000 / + 2505325 / x 10157200 / - + 849291000 / x 43711000 / - + / + / + / - / - / + :

OACI uncorrected altitude[m] vs  kPa kPa OACI 576300140 kPa * 4053 / ln 5.255 / exp - (* 13 / :

22.272 Thiele 22.272 OACI 21 mat 111021110321 mat

80 Thiele 80 OACI 21 mat 1949194921 mat

90 Thiele 90 OACI 21 mat 98898921 mat

<p> TableIII Piot Data</p>

..... -10,210 is in error .....

TableIII 15008515021528536545012007012017023029036090050901301702202706003560851151451804502545658511013530020304560759027015304055658024015253545607521015253040506518010202535455515010152530404512010152025304090510152025306051010151520147 mat :

header m 0°C -10°C -20°C -30°C -40°C -50°C augment :

TableIII header TableIII stack :

TableIII m 0°C -10°C -20°C -30°C -40°C -50°C 15008515021528536545012007012017023029036090050901301702202706003560851151451804502545658511013530020304560759027015304055658024015253545607521015253040506518010202535455515010152530404512010152025304090510152025306051010151520157 mat

approach TableIII 1 col TableIII 4 col augment :

@ those low approaching altitude
°C runway is assumed constant.
If you re-coorect @ lower altitude,
uncorrect the previous altitude.
See Chevron pilot procedure. approach m -20°C 1500215120017090013060085450653004527040240352103018025150251202090156010152 mat

Specific 'ρ' @ km altitude ...

ISA 0.5 - 1.0489 01 0.5 0.9529 1 0.9075 1.5 0.8638 2 0.8217 2.5 0.7812 3 0.7422 3.5 0.7048 4 0.6689 4.5 0.6343 5 0.6012 5.5 0.5694 6 0.5389 6.5 0.5096 7 0.4816 7.5 0.4548 8 0.4292 8.5 0.4047 9 0.3813 9.5 0.3589 10 0.3376 10.5 0.3172 11 0.2978 11.5 0.2755 12 0.2546 12.5 0.2354 13 0.2176 13.5 0.2012 14 0.186 14.5 0.172 15 0.159 15.5 0.147 16 0.1359 16.5 0.1256 17 0.1162 17.5 0.1074 18 0.0993 18.5 0.0918 19 0.0849 19.5 0.0785 20 0.0726 25 0.032 30 0.015 32 0.011 35 0.006705 40 0.003144 45 0.001536 47 0.001165 50 0.000798 52 0.00062 55 0.000432 60 0.000233 61 0.000205 71 0.00005242 85 0.00000568 562 mat :

data char size clr plot k 1 data rows range r3 k el char : r4 k el size : r5 k el clr : 13 mat for data r3 r4 r5 augment 21 line :

L H N xd U 0 : dx H L - N / : i 1 N 1 + range U i el L dx - (dx i * + : for U 41 line :

X ISA 1 col : Y ISA 2 col : 21 line

Much better fit to PDAS x ρ20 0.0001376 1.67547 x 6.36715 / - exp * + :

Low computing cost  from MCD 11 NLRF converted x ρ11 1.604858 174.727169 x 43.473225 + 1286.481982 x 5.24242 + 0.000159 x 5.14073 - / + / + / - :

β 1.30644000006 104 -^* 38518.8995295 38510.6720344 64.7372080910 68.7237058260 25.4827261347 4.84161810338 105 -^* 1483390476.38 2.74067434956 2.79372428294 575.381616331 111 mat :

'β' Collected from Mathcad 11 x J β 1 el β 7 el x β 2 el + β 8 el x β 3 el - β 9 el x β 4 el - β 10 el x β 5 el - β 11 el x β 6 el - / + / + / + / + / + :

ρ11 xy ISA 124 range 12 range el : i 1 xy rows range u11 i el xy i 1 el : U11 i el u11 i el ρ11 : 21 line for u11 U11 augment 31 line :

ρ20 xy ISA 2542 range 12 range el : i 1 xy rows range u20 i el xy i 1 el : U20 i el u20 i el ρ20 : 21 line for u20 U20 augment 31 line :

ρ85 xy ISA 4356 range 12 range el : i 1 xy rows range u85 i el xy i 1 el : U85 i el u85 i el J : 21 line for u85 U85 augment 31 line :

ρISA ρ11 ρ20 ρ85 stack :

P ρISA . 12 black plot :

x λ11 1 0.5 - x ≤ (x 11 ≤ (& cases :

x λ20 111 x ≤ (x 20 ≤ (& cases :

x λ85 120 x ≤ (x 85 ≤ (& cases :

x ρ11 x λ11 * x ρ20 x λ20 * x J x λ85 * P 20 0.375 specific ρ [ISA] @ km altitude 20 brown 1 5 mat 5 1 sys

kgm³ 1 :

11 ρ20 1.225 * kgm³ 0.3649

The all thing is solving for 'M' that appears on both sides. Hre comes the power of Smath solving as given, solving on the canvas.

γ 1.4 : (Air isentropic ≡ k 0.88128485 : (Pitot constant ≡ p static pressure ≡ qc dynamic pressure ≡ x Pitot dynamic ratio qc/P ≡ x qc p / ≡ (supersonic Pitot ratio ≡ 61 line

Observe the canvas solutions:

as 'x' in Supersonic(x) runs on the plot canvas,

the 'roots' solves and plots each canvas pixel result ...

each result on the basis of 96 ppi [pixel per inch].

]]>

Plot limit x c 1 k x ≤ (x 4 ≤ (& cases :

t0 1 time :

x Subsonic 2 γ 1 - / (x 1 + (γ 1 - γ /^1 - (* sqrt 0 x ≤ (x k ≤ (& Supersonic cases : x Supersonic U x 1 + (117 U 2^* / - (2.5^* sqrt / k - 0 ≡ U 1 roots k x ≤ Subsonic cases : 21 line

x Subsonic x Supersonic x c * k 1 + 40 black 1 5 mat 3 1 sys

1 time t0 - 69 s *

supersonic

subsonic

Thiele executable global fit ...

Overall Mach subsonic-supersonic ... a damned super-reconciliation x f 14.2683 1189.48 x 98.2703 + 66.9393 x 6.74479 + 0.726987 x 0.367336 + 0.043852 x 0.470545 - 0.293801 x 0.0549761 - 0.00515151 x 0.0199953 + / + / + / - / - / - / - :

Differential ... exact-Thiele fit

0.0125 k * Subsonic 0.0125 k * f - 0.25 k * Subsonic 0.25 k * f - 0.5 k * Subsonic 0.5 k * f - 0.75 k * Subsonic 0.75 k * f - 0.95 k * Subsonic 0.95 k * f - k Subsonic k f - 61 mat 0.0044 0.0001 - 0.0001 0.0000 0.0003 0.0003 61 mat

k Supersonic k f - 2 Supersonic 2 f - 3 Supersonic 3 f - 5 Supersonic 5 f - 15 Supersonic 15 f - 20 Supersonic 20 f - 61 mat 0.0003 0.0000 0.0003 0.0000 0.0000 0.0001 61 mat

speed of sound at sea level = 340.29 m/s

The static ports of Pitot tube are always multiple. The principle behind is ChebyShev kind of averaging. A similar technique applies to "Annubar" a flow measuring device for dirty fluids.

Solving Pitot ratio 'x' given Mach(U)

Pitot_sub(U) . . . Pitot_sup(U)

]]>

U Pitot_sub 1 - 2 U 2^γ * + U 2^- 2 / ln γ * 1 - γ + / exp + :

x sub 10 x ≤ (x 1 ≤ (& cases : x sup 11 x ≤ (x 2 ≤ (& cases : 21 sys

Explicit Pitot ratio 'x' 
from given Mach = U U Pitot_sup k 2^17 U 2^* 3 - 7 U 2^* 37 U 2^* - (* + (* + (* 49 U 8^* 1 - 7 U 2^* + U 2^/ sqrt * 7 sqrt * + 1 - 7 U 2^* + (k 2^* 17 U 2^* 2 - 7 U 2^* + (* + (* / :

subsonic
hyersonic 0.75 Pitot_sub 5 Pitot_sup 21 sys 0.452 31.653 21 sys

unknown interest: Find Pitot 'x' <= Given Mach 'U'

x Pitot_sub x sub * x Pitot_sup x sup * 1 k + 20 black 1 5 mat 3 1 sys

jmG: 20230429