Flight 1784
Lil Nuke - Flight with 4 altimeters - 1
Mercury V1 Rev 3 · firmware 2.40
Apogee
756.82m
11.48 s after launch
Max ascent
155.99m/s
peak ascent
Max during burn
17.26G
during the burn
Landing
129.36s
touchdown 7.02 m/s
ZOOM TO
s
s
Flight summary
The flight, moment by moment
Liftoff
0 s
Launch pad tilt1.56°
Thrust calc pad tilt2.3°
Launch detected
0.597 s
Altitude25.05 m
Velocity65.05 m/s
Burnout (first)
1.39 s
Altitude119.99 m
Velocity155.880 m/s
Possible ejection
1.993 s
Altitude210.8 m
Velocity133.63 m/s
Apogee
11.48 s
Altitude756.82 Meters
Max tilt to burnout19.87°
Landing
129.36 s
Altitude-1.97 m
Max descent-10.38 m/s
Stability85.9%Excellent
Launch straightness (20%)94.1
20% · Launch tilt 2.3°
Coning · full (25%)93.9
25% · Coning 25.3/53°/s
Coning · boost (25%)78
25% · Spin 441.3°/s
Thrust straightness (30%)80.5
30% · Thrust 95.9%
Rocket information
Calculated from the flight data alone
Boost acceleration112.1 m/s²
average over the burn · 11.4 g
Coast deceleration15.4 m/s²
average · gravity plus drag
Ballistic coefficient535 kg/m²
fitted to the 10.09 s coast
Apogee lost to tilt0.6 m
flown vertical ≈ 757.4 m · from the thrust-calculated tilt
Chute opening peak43.96 G
largest deceleration after ejection
Average descent rate1.67 m/s
ejection to landing · 127.37 s
Battery & temperature 90% → 82% · Temperature start 27.1 → 28.41 °C · Launch after startup 7m 8s
Altitude
Apogee756.82 Meters
Time to apogee11.48 s
Burnout altitude119.99 m
Max velocity altitude137.51 m
Ejection altitude210.8 m
Landing altitude-1.97 m
Recording altitude41.06 m
Velocity
Max ascent155.99 m/s
Max descent-10.38 m/s
At burnout155.880 m/s
Descent velocity-6.438 m/s
Ejection velocity133.63 m/s
Landing velocity-7.016 m/s
Acceleration
Max during burn17.26 G
Max ascent31.05 G
Max descent43.96 G
Average ascent1.23 G
Average burn12 G
Times
Burnout (first)1.39 s
Apogee11.48 s
Possible ejection1.993 s
Landing129.36 s
Output #1 ON0 s
Output #1 OFF0 s
Angles
Launch pad tilt1.56°
Thrust calc pad tilt2.3°
Max tilt to burnout19.87°
Launch roll-0.42°
Launch pitch-1.50°
Max spin (burn)1332.99 dps
Avg spin (burn)324.26 dps
Recovery
Single deploy
No dual deploy detected on this flight.
General
Upload date14-Jun at 14:55
Data samples12578
Total recording time155.000 s
Average samples/s81.1
Number of lockouts0
Launch after startup7m 8s
Reference axisX
Battery & temperature
Battery start90%
Battery end82%
Temperature start27.1°C
Temperature end28.41°C
MT1 launch temp0°C
Output rules
No rules configured
User notes
A test of 2x Mercury and 2x Nano altimeters in a Lil Nuke with a G80 Aerotech motors.
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Youtube video
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Flight images 0
No images added
Flight motors
1st stage · 10s delay
Burn time
1.7 s
Diameter
29.00 mm
Average thrust
77.6 N
Max thrust
108.5 N
Total weight
127.90 g
Propellant weight
62.50 g
Propellant type
Blue Thunder
Links
Impulse136.6Ns
Max thrust108.5N
Burn time1.7s
Impulse classG
1st stage thrustloading curve…
Motor data by ThrustCurve.org
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Linked rocket
Active
1 photo
My Lil Nuke #1
LOC Precision — Lil' Nuke
Type
Kit build
Diameter
57.4mm
Length
749.3mm
Dry weight
368.5g
Mod
Modified
Stages
1
Fins
3
Recovery
Parachute
Chute
61cm
Body
Loc paper tube
Sim data from sim files
| Motor | Alt | Vel | Accel | Apogee | Source |
|---|---|---|---|---|---|
| Estes A8-3 | 135.3 m | 64.8 m/s | 29.6 G | 4.5 s | RockSim (estes_viking.rkt) |
| Estes B4-4 | 282.9 m | 105.3 m/s | 30.0 G | 6.1 s | RockSim (estes_viking.rkt) |
| Estes B6-4 | 288.1 m | 116.9 m/s | 31.0 G | 5.9 s | RockSim (estes_viking.rkt) |
| Estes C6-5 | 475.1 m | 171.4 m/s | 34.4 G | 7.5 s | RockSim (estes_viking.rkt) |
| Estes C6-7 | 483.1 m | 171.4 m/s | 34.4 G | 8.1 s | RockSim (estes_viking.rkt) |
Other flights on this motor
7 · highest first
Lil Nuke - G80-10 - altimeter 3/4
823.1m
Lil Nuke - G80-10 - altimeter 4/4
823.1m
Lil Nuke - G80-10 - altimeter 2/4
822.9m
Lil Nuke - G80-10 - altimeter 1/4
822.8m
Lil Nuke - Flight with 4 altimeters - 4
756.8m
Lil Nuke - Flight with 4 altimeters - 2
756.7m
Lil Nuke - Flight with 4 altimeters - 3
756.7m
Rule events
No output rules fired during this flight.
Motor match (BETA)
Very much in testing mode! We are working out how to guess which motor a flight flew on.
Brand
Motor
Score
Shape
Burn
AeroTech
J615ST
142
92.9%
97.5%
AeroTech
H195NBT
110
81.5%
96.9%
Cesaroni
G118-BS
105
83.5%
95.9%
Cesaroni
G125-RL
104
84.3%
94.4%
AeroTech
I600R
104
82.8%
91.1%
AeroTech
J825R
104
84.7%
94.7%
Cesaroni
H163-WT
100
82%
95.5%
Cesaroni
G83-BS
99
84.1%
94.3%
Cesaroni
H133-BS
99
86%
94.2%
Cesaroni
H255-BS
99
85.8%
91.3%
Linked flights
No linked flights yet.
Launch site, date & time
Imagery © Esri, Maxar, Earthstar Geographics
Click the map to place a marker · Drag to adjust
Canopy height from the Meta and WRI High Resolution Canopy Height Maps v2 (Meta and World Resources Institute, 2026; source imagery © 2016 Vantor), used under CC BY 4.0. Ground elevation built from Terrain Tiles (Mapzen and AWS Open Data), derived from 3DEP and GMTED courtesy of the U.S. Geological Survey, SRTM courtesy of NASA, and ETOPO1 courtesy of NOAA. Map and imagery credited on the view above.
Site nameUnnamed siteLat52.668772Lng-1.523783Ground level106.4 m · 349 ftLaunch date2026-06-14Launch time14:00
Taken from the NOAA GFS weather model for this place and time, so there is nothing to enter. Weather data by Open-Meteo.com (CC BY 4.0). The full weather for 48 hours either side, within 15 km, is in the tabs below and in Downloads.
Temperature17.6 °C
Sea-level pressure1019.9 hPa
QNH1020 hPa
Wind speed4 m/s
Wind directionNW
Cloud coverOvercast
About sea-level pressure and QNH
Sea-level pressure is kept as given: the model’s own, or the figure entered from a forecast or report. QNH is that pressure the way an altimeter setting means it, through the standard atmosphere, and is what the adjusted apogee and the adjusted CSV use.
Model values, not observations. NOAA GFS: weather data by Open-Meteo.com (CC BY 4.0). Ensemble: NOAA GEFS.
Flight data animation
FLIGHT 1784
756.82 Meters
ALTITUDE
0.00m
VELOCITY
0.00m/s
ACCEL
0.00G
TILT
0.00°
PITCH
0.00°
ROLL
0.00°
YAW
0.00°
TIME
0.00s
AWAITING LAUNCH
ALT
altimetercloud.com
LAUNCH
T+0.00s
LANDING
BURNOUT
Motor burn complete
Note: Flight profile animation requires your altimeter to be mounted in a fixed orientation that you choose in your settings. For best results please calibrate your sensors as well.
Mercury V1
This flight was flown on a Mercury V1.
The hardware
Hardware versionRev 3
Software version2.40
Last online14-Jun at 14:55
Pressure sensorBosch BMP 581
Accelerometer32G 3-axis
Gyroscope2000 dgps 3-axis
MagnetometerN/A
Flights from this altimeter
No other flights yet. This will fill up as you fly.
Settings, as they were for this flight
General flight settings
Forecast pressure
i
Set this to your local forecast pressure at sea level. This will offer you slightly improved accuracty for your flight, although it's not 100% essential every little helps!
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
Xcweather.co.uk is a decent place to grab pressures from for your location and time.
1013.2 mbar
Launch detect
i
This is the altitude above the launch pad altitude where the altimeter will trigger itself into recording / flight mode.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
The altimeter keeps a constant average of the pressure while waiting for launch, it uses a simple algorithm and the pre-flight buffers to do this. The most recent 120 samples (~4 seconds) are ignored so your pre-trigger altitude won't effect the ground baseline.
For almost all uses we suggest keeping this on the 25 Meter (~82 feet) default settings. If you want to test your altimeter by throwing it in the air, or are planning a very low flight you may want to lower the setting.
25
meters
Sample ratio
i
The altimeter runs at 50Hz however you can record every sample or every X samples in order to extend the log time. For example if you set the ratio to 1 it will save 1:1 samples, or if you set it to 3 it will save 1 in 3 samples.
1:5 (hybrid, reduces after apogee)
Max samples
i
This is the maximum samples the altimeter will log per flight. When it reaches this amount it will stop and save the recording.
18000
Recording stop
i
This setting is how the altimeter decides to stop recording. You can choose either 450 (~9s) or 900 (~18s) samples stable or it will record until the max samples limit unless you press the BUTTON in Manual stop mode.
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
The samples stable method waits for the devices altitude not to change for the set number of samples. This is defined by not changing by more than +/- 1.0 meters for 98% of the samples, it's a reliable method to stop the recording after landing within 8-10 seconds (300 sample) or 16-20 seconds (600 sample).
Auto: 450 samples stable (~9s)
Oversampling
i
Oversampling is a internal setting of the BMP 390 pressure sensor. It is how many samples are taken for each reading. By taking multiple samples for each pressure reading the altimeter reduces noise and increases the resolution of the output.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
The sensor can run at 50 samples per second in 4X mode, so we suggest leaving it in this mode as it will offer the highest accuracy.
16x Oversampling
IIR filter
i
The IIR filter is another internal sensor for the BMP390 pressure sensor. It is a Infinite impulse response filter used to enhance pressure measurement accuracy by reducing noise. It's primarily for smoothing out rapid pressure changes.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
We suggest not setting this too high as it will cause delay to changes in altitude if set very high.
COEFF 7
Pressure filter
i
This filter is a software Kalman filter that runs on the altimeters processor.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
The Kalman filter uses a prediction step based on a system model and then a correction step using new measurements to refine its estimate, it creates accurate most certain results from data with noise in it.
Kalman 2 (default)
Lockout change
i
This is how we detect a lockout. If the pressure changes by this much in a single sample downwards (pressure increase, lower altitude) then it's likely to be a false reading. Multiply the setting by 32 to get the speed in meters per second that it will trigger at.
0.5 meters
Sync sensors
i
The filters on the pressure sensor can cause it to lag very slightly behind the Accelerometer and Gyroscope data.
The Sync sensors option detects how far out of sync these sensors are. It then corrects the Acceleration and Gyroscope readings to match the pressure sensor.
ENABLED (17 samples / 88.00ms)
Orientation
i
This is the orientation you intend to install the Altimeter in your rocket. It's needed to ensure completly accurate angles and orientation charts and reports. Check out the Manual for more information on this.
Upwards (text up)
IMU filter
i
The IMU filter, or fusion filter takes the data from each axis of the Gyroscope and Accelerometer to calculate the Pitch, Roll, Yaw and tilt angle from vertical.
These filters can build up some discrepency over time so it's important to calibrate your sensors to minimise this.
Madgwick 6-Axis
Launch ALP
i
This is prevention against accidental launch detection.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
With this disabled the launch is based only on pressure and something that creates a low pressure can trigger the flight by accident. For example pulling your nose cone off can even trigger it.
With this enabled the rocket also needs to have seen 8 samples (0.25 seconds) of acceleration above this setting in the last 3 seconds as well as the pressure drop to trigger. There is a backup trigger of 1.05 seconds of altitude being above the launch detect setting too.
There are very few situations where this option would cause issues, so we suggest leaving it on.
1.4G
Launch lock
i
When enabled, the altimeter locks out recording for a set period after power on to prevent false triggering during setup.
DISABLED
Static temperature
i
A fixed temperature value used for altitude calculation when the external temperature sensor is disabled or not connected.
15.00 °C
Temp sensor
i
If an external MT1 temperature sensor is connected, this controls whether it is used for logging only or also for altitude calculations.
DISABLED
Output settings
Arm switch
i
When enabled, GP6 is a hardware arm switch — outputs and rules are held off until the switch is closed to ground.
DISABLED
Startup lockout
i
Outputs and rules are blocked for this many seconds after power-on while sensors settle. 0 = off.
None
Launch confirm delay
i
After launch is detected, outputs and rules won't fire until this many seconds have passed.
—
Altitude floor
i
Outputs and rules are blocked until the rocket is at least this height above the launch pad.
—
Custom dataset 1
i
User-defined expression evaluated per sample, available for charting.
—
Custom dataset 2
—
Sensor calibration
Calibration offsets used during this flight.
Gyroscope
X0.180°
Y0.140°
Z1.000°
Accelerometer
X23.010 mG
Y3.090 mG
Z27.650 mG
Device settings
Device TAG
i
A custom name or tag assigned to this device for easy identification.
TEST-RIGHT-4
Language
i
The language setting configured on the device.
🇬🇧 English
Shutdown mode
i
Controls what happens after recording. Standard shuts down normally, Delayed keeps WiFi on for 30 seconds after landing, Stay on keeps the device powered on.
Delayed 30s
LED brightness
i
The brightness level of the LED indicators on the Mercury. Lower values save battery.
20%
WiFi TX power
i
WiFi transmit power level. Higher gives better range but uses more battery.
2 dBm (low)
Sleep mode
i
Controls whether the device enters low-power sleep when idle.
Normal (sleep when idle)
Battery monitor
i
Monitors battery voltage during the flight.
DISABLED
Cloud group
i
The cloud group / category this flight is assigned to.
GP6 / GP7 ports
Configuration for the GP6 and GP7 general purpose output ports. These ports can drive pyro channels, servos, or other devices.
Channel 6 mode
ON = HIGH
Ch6 min pulse (µs)
0
Ch6 max pulse (µs)
0
Ch6 frequency
0 Hz
Ch6 angle ON
0.00°
Ch6 angle OFF
0.00°
Ch6 on time
0.00s
Channel 7 mode
ON = HIGH
Ch7 min pulse (µs)
0
Ch7 max pulse (µs)
0
Ch7 frequency
0 Hz
Ch7 angle ON
0.00°
Ch7 angle OFF
0.00°
Ch7 on time
0.00s
I2C PCA9685 Servo Board
Configuration for the external I2C PCA9685 servo expansion board. This board provides up to 6 additional servo channels.
No I2C servo board was connected for this flight.
Prediction and air brakes
The Mercury can predict apogee while coasting after burnout. These settings control the prediction calculation and optional air brake system.
Dry mass
i
The total mass of the rocket after motor burnout (dry mass). This is used for the ballistic prediction of apogee altitude. Enter the mass without the motor propellant, or the mass at burnout.
$tc_not_configured
Drag Cd
i
The aerodynamic drag coefficient (Cd) of the rocket. This is used with the rocket area to calculate aerodynamic drag during coast. A typical model rocket has a Cd of 0.4 to 0.8. You can find this value from OpenRocket or RockSim simulations.
$tc_not_configured
Reference area
i
The cross-sectional reference area of the rocket in square meters. This is typically the area of a circle with the body tube diameter. For example a 38mm tube has an area of approximately 0.00113 m².
$tc_not_configured
Gas constant
i
The specific gas constant for dry air, used in the atmospheric model for altitude and density calculations. The standard value is 287.05 J/(kg·K). You shouldn't need to change this unless you know what you're doing.
$tc_not_configured
The following settings configure the air brake system.
Air brake enabled
i
Enables or disables the active air braking system. When enabled, the Mercury will deploy air brakes via the configured servo channel to try and reach the target altitude. Firmware 2.1+ required.
OFF (default)
Servo channel
i
Which servo output channel the air brake mechanism is connected to. GP6 and GP7 are the two onboard servo headers, I2C channels are for an external servo expander board.
GP6
Deploy speed
i
The speed at which the air brakes deploy. The Mercury gradually increases the servo angle until the predicted apogee matches the target rather than going full on/off. This setting controls how quickly it ramps up to full braking.
Medium (default)
Target altitude
i
The target apogee altitude in meters. The air brake system will try to slow the rocket so it reaches this altitude.
$tc_not_configured
Over shoot %
i
The percentage over the target altitude to aim for until within 15% of the target. This helps prevent undershooting if the prediction is slightly off early in the coast. For example, with a 1000m target and 5% early adjustment, the Mercury will aim for 1050m until it passes 850m.
$tc_not_configured
Activation altitude
i
The air brake system activates after burnout, but won't engage until the rocket has reached this percentage of the target altitude. This prevents the brakes from deploying too early when predictions may be less accurate.
20% (default)
Files
Where the altimeter signs its log, the file carries that signature and a tick beside it. A tick means the data is unchanged since the device wrote it, which is what a record claim needs.
CSV
1784.csv
The log as columns of text. Opens in a spreadsheet, and in every simulator that reads flight data.
1033 KB
WX
1784_weather.json.gz
The weather for 48 hours either side of the launch, within 15 km of the launch site: NOAA GFS every hour, at the surface and up to about 31 km, and the NOAA GEFS ensemble where this site holds it. JSON, gzip compressed. Weather data by Open-Meteo.com (CC BY 4.0) and NOAA. For 2026-06-14 14:00 local time at 52.6688, -1.5238.
197 KB
Adjusted CSV2904 recalculated in your browser
The log recomputed for your own sea-level pressure and temperature. Columns: time, altitude as recorded and adjusted, raw altitude as recorded and adjusted, pressure.
This file is built here from the signed log, so it carries no signature of its own. Anyone verifying a claim should be sent to the flight page and build their own from the original.
Share this flight
Anyone with the link can view this flight; nothing else on your account is shared.
Chart snapshot
A PNG of the chart exactly as you have it set right now: the series you have switched on, your zoom, your labels and any pressure correction applied.
Hotlink images
Stored images of the whole flight, altitude only, not your current chart view. Transparent, regenerated whenever the flight changes, and safe to hotlink on a forum.
QR code
Links to this flight page. Useful on a range card or a club display.
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