# Performance Specs

## Performance Charts

### Flight Time v. Payload

![](/files/Sd18qhERv7eZzLbrYz5d)

### Thrust-to-weight ratio

| **Flight Time (min)** | **Payload (lbs)** | **Payload (kg)** | **Total Weight (lbs)** | **Thrust to Weight Ratio** |
| :-------------------: | :---------------: | :--------------: | :--------------------: | :------------------------: |
|           50          |         0         |         0        |          43.28         |             3.5            |
|          41.7         |         5         |        2.3       |          48.28         |             3.1            |
|          33.3         |         10        |        4.5       |          53.28         |             2.8            |
|          26.6         |         15        |        6.8       |          58.28         |             2.6            |
|           22          |         20        |        9.1       |          63.28         |             2.4            |
|           18          |         25        |       11.3       |          68.28         |             2.2            |
|          12.5         |         30        |       13.6       |          73.28         |             2.0            |
|         10.75         |         35        |       15.9       |          78.28         |             1.9            |

### Maximum Gross Weight

To determine maximum gross weight, determine flight location pressure altitude, and temperature, and refer to the weight in the chart below.
 Gross Weight includes payload, battery, and structure weight.

The maximum gross weight might exceed the weight allowed by regulatory agencies. When determining gross weight, please consider any such local restrictions on aircraft weight when planning aircraft weight.

{% hint style="info" %}
The maximum gross weight at a defined density altitude was established by calculating weight so that sufficient thrust margin for maneuvering is maintained.
{% endhint %}

![](/files/7x9DgxmOM4LdzC6HEola)

{% hint style="info" %}
Cells highlighted in yellow indicate where the weight is limited by the maximum design weight
{% endhint %}

<table data-header-hidden><thead><tr><th width="251">Max Configurable Parameters</th><th align="right"></th></tr></thead><tbody><tr><td><strong>Max Configurable Parameters</strong></td><td align="right"></td></tr><tr><td>Max Angular Velocity</td><td align="right">Configurable, default to 100 deg/s in manual mode</td></tr><tr><td>Max Pitch Angle</td><td align="right">Configurable, default to</td></tr><tr><td>Max Ascent Speed (by mode)</td><td align="right">Configurable, default to 6m/s in Position &#x26; Altitude Mode</td></tr><tr><td>Max Descent Speed (vertical (by mode)</td><td align="right">Configurable, default to 4m/s down in Position &#x26; Alt Mode</td></tr><tr><td>Max Speed (by mode)</td><td align="right">Configurable, default to 20m/s in Position Mode</td></tr><tr><td>Max Service Ceiling above Sea Level</td><td align="right">Depends on payload, see "Maximum Gross Weight" chart</td></tr></tbody></table>


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