Ballistic Drop Calculator
Bore elevation above the line of sight
3.360 MOA
Ballistic Trajectory Calculator
Launch angle above the line of sight
0.05600 deg
Muzzle energy
3,356.7 ft-lbf
Muzzle Mach number
2.6871
Velocity at the far end of the table
1,951.7 ft/s
Energy at the far end of the table
1,420.7 ft-lbf
Drop below the bore line at the far end
93.29 in
Bullet path at the far end
-73.68 in
Wind drift at the far end
0.00 in
Time of flight to the far end
0.7448 s
Highest point above the line of sight
0.04 in
Range of the highest point
86 yd
Air density used
0.076474 lb/ft^3
Speed of sound used
1,116.45 ft/s
Worked out from JBM Ballistics, drag function downloads - machine-readable CD vs Mach tables for the G1 and G7 standard projectiles and 3 other sources.
Spin drift, Coriolis, aerodynamic jump and transonic instability are not modelled, and the ballistic coefficient is held constant with velocity.
A physics model, not a firing solution. It ignores spin drift, Coriolis, aerodynamic jump and transonic behaviour, and it assumes the ballistic coefficient you enter is constant. Confirm every setting on paper at a safe range before relying on it, and follow all applicable firearms law and range safety rules.
How this is worked out
5 steps
- Atmosphere: 15 C, 29.9213 inHg, 0% RH gives air density 0.076474 lb/ft^3 and a speed of sound of 1116.45 ft/s.
- Drag deceleration = (pi/1152) x rho x CD(M) x |v|^2 / BC = 0.0004171 x CD(M) x |v|^2 ft/s^2.
- Elevation solved so the path crosses the line of sight at 100 yd: 3.36 MOA above the line of sight.
- Muzzle energy = 1/2 x 168 gr x 3000 ft/s squared = 3356.7 ft-lbf.
- At 600 yd: 1951.7 ft/s, 1420.7 ft-lbf, 0.7448 s of flight, 93.29 in of drop and a path -73.68 in relative to the line of sight.
Trajectorytable
| rangeYards | velocityFps | machNumber | energyFtLb | timeSeconds | dropInches | pathInches | windDriftInches | holdoverMoa | holdoverMil |
|---|---|---|---|---|---|---|---|---|---|
| 0 | 3,000 | 2.687 | 3,356.7 | 0 | 0 | -1.5 | 0 | 0 | 0 |
| 50 | 2,902.2 | 2.599 | 3,141.4 | 0.0508 | 0.49 | -0.23 | 0 | 0.45 | 0.13 |
| 100 | 2,806.5 | 2.514 | 2,937.7 | 0.1034 | 2.02 | 0 | 0 | -0 | -0 |
| 150 | 2,712.9 | 2.43 | 2,745.1 | 0.1578 | 4.65 | -0.87 | 0 | 0.55 | 0.16 |
| 200 | 2,621.3 | 2.348 | 2,562.8 | 0.214 | 8.46 | -2.92 | 0 | 1.39 | 0.41 |
| 250 | 2,531.5 | 2.267 | 2,390.3 | 0.2722 | 13.53 | -6.23 | 0 | 2.38 | 0.69 |
| 300 | 2,443.6 | 2.189 | 2,227 | 0.3325 | 19.96 | -10.91 | 0 | 3.47 | 1.01 |
| 350 | 2,357.3 | 2.111 | 2,072.6 | 0.395 | 27.85 | -17.03 | 0 | 4.65 | 1.35 |
| 400 | 2,272.8 | 2.036 | 1,926.6 | 0.4599 | 37.3 | -24.72 | 0 | 5.9 | 1.72 |
| 450 | 2,189.9 | 1.962 | 1,788.7 | 0.5271 | 48.43 | -34.1 | 0 | 7.24 | 2.1 |
| 500 | 2,108.8 | 1.889 | 1,658.6 | 0.5969 | 61.38 | -45.28 | 0 | 8.65 | 2.52 |
| 550 | 2,029.3 | 1.818 | 1,536 | 0.6694 | 76.28 | -58.42 | 0 | 10.14 | 2.95 |
| 600 | 1,951.7 | 1.748 | 1,420.7 | 0.7448 | 93.29 | -73.68 | 0 | 11.73 | 3.41 |
Results are general information, not financial, tax, legal, medical or engineering advice.