blackbrandt
That Darn College Student
- Joined
- Mar 18, 2012
- Messages
- 9,281
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OK, so this is gonna sound confusing, but hear me out.
I am getting data out of Openrocket to run through a program called R. The data I am trying to get out of OR looks like this:
The rocket in this simulation is powered by 3 different hypothetical motors (I made the thrust curves myself, they are basically constant thrust motors with equal weights and stuff) that cause the rocket to go subsonic, transonic, and supersonic speeds.
The length is the length of the nose cone.
The L/W ratio is the length to width ratio of the nose cone.
The Max Vel C_D is the coefficient of drag at the maximum velocity obtained during flight.
The final altitude is self explanatory.
How I have been getting this data is editing the nose cone length, and running 3 simulations (1 with each motor), copying down the altitude, and then estimating the Cd using the graph from the simulation.
Is there any way I can have openrocket do this automatically? Essentially, I want it to say
Nose cone length: 3.1 --> Max altitude: x feet
Nose cone length: 4.1 --> Max altitude: y feet
Nose cone length: 5.1 --> Max altitude: z feet
Here is what I have done so far.
Does this make any sense or am I just confusing everyone?
I am getting data out of Openrocket to run through a program called R. The data I am trying to get out of OR looks like this:
The rocket in this simulation is powered by 3 different hypothetical motors (I made the thrust curves myself, they are basically constant thrust motors with equal weights and stuff) that cause the rocket to go subsonic, transonic, and supersonic speeds.
The length is the length of the nose cone.
The L/W ratio is the length to width ratio of the nose cone.
The Max Vel C_D is the coefficient of drag at the maximum velocity obtained during flight.
The final altitude is self explanatory.
How I have been getting this data is editing the nose cone length, and running 3 simulations (1 with each motor), copying down the altitude, and then estimating the Cd using the graph from the simulation.
Is there any way I can have openrocket do this automatically? Essentially, I want it to say
Nose cone length: 3.1 --> Max altitude: x feet
Nose cone length: 4.1 --> Max altitude: y feet
Nose cone length: 5.1 --> Max altitude: z feet
Here is what I have done so far.
Does this make any sense or am I just confusing everyone?
Length | L/W Ratio | Max Vel C_D Subsonic | Final Altitude Subsonic | Max Vel C_D Transonic | Final Altitude Transonic | Max Vel C_D Supersonic | Final Altitude Supersonic |
3.1 | 1.00 | 0.843 | 9040 | 1.032 | 7557 | 1.198 | 6798 |
4.1 | 1.32 | 0.785 | 9387 | 0.959 | 7937 | 0.997 | 7223 |
5.1 | 1.65 | 0.753 | 9561 | 0.908 | 8142 | 0.868 | 7480 |
6.1 | 1.97 | 0.726 | 9728 | 0.869 | 8319 | 0.783 | 7696 |
7.1 | 2.29 | 0.704 | 9868 | 0.837 | 8477 | 0.727 | 7887 |
8.1 | 2.61 | 0.689 | 9941 | 0.813 | 8571 | 0.690 | 8007 |
9.1 | 2.94 | 0.677 | 10006 | 0.795 | 8674 | 0.659 | 8125 |
10.1 | 3.26 | 0.666 | 10075 | 0.779 | 8754 | 0.638 | 8219 |
11.1 | 3.58 | 0.659 | 10079 | 0.767 | 8798 | 0.631 | 8276 |
12.1 | 3.90 | 0.650 | 10131 | 0.757 | 8847 | 0.619 | 8336 |
13.1 | 4.23 | 0.644 | 10158 | 0.749 | 8892 | 0.611 | 8389 |
14.1 | 4.55 | 0.639 | 10149 | 0.742 | 8930 | 0.604 | 8428 |
15.1 | 4.87 | 0.635 | 10214 | 0.737 | 8958 | 0.598 | 8461 |
16.1 | 5.19 | 0.633 | 10151 | 0.732 | 8970 | 0.593 | 8477 |
17.1 | 5.52 | 0.630 | 10160 | 0.728 | 8987 | 0.589 | 8500 |
18.1 | 5.84 | 0.627 | 10198 | 0.725 | 8999 | 0.587 | 8519 |
19.1 | 6.16 | 0.625 | 10140 | 0.722 | 9015 | 0.584 | 8532 |