Formulas: Test Levels and Conditions - Fighter and Attack Aircraft

MIL-STD-810H, Environmental Engineering Considerations and Laboratory Tests

Last Updated 29 Oct 2026

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Formula 1

\Delta N_{Z} = (z/g) (d\ \phi / d\ t)^{2} + (y/g) d^{2} \phi / d\ t^{2}

\phi$/$d$ t$^{2}$ - c. Pitch maneuver, up and down test directions. The additional load factor (ΔNz) induced by pitch change, is computed as follows: $\Delta \mathrm{N}_{\mathrm{z}}=(\mathrm{z} / \mathrm{g})(d \theta / d \mathrm{t})^{2}+(\mathrm{x} / \mathrm{g}) d^{2} \theta / d \mathrm{t}^{2}$ - d. Pitch maneuver, fore and aft test directions. The additional load factor (ΔNx) induced by pitch change, is computed as follows:

MIL-STD-810H, Environmental Engineering Considerations and Laboratory Tests

Last Updated 29 Oct 2026

Hover any section to copy its link or text, ask Copilot about it, or bookmark it.

\Delta N_{Z} = (z/g) (d\ \phi / d\ t)^{2} + (y/g) d^{2} \phi / d\ t^{2}

\phi$/$d$ t$^{2}$ - c. Pitch maneuver, up and down test directions. The additional load factor (ΔNz) induced by pitch change, is computed as follows: $\Delta \mathrm{N}_{\mathrm{z}}=(\mathrm{z} / \mathrm{g})(d \theta / d \mathrm{t})^{2}+(\mathrm{x} / \mathrm{g}) d^{2} \theta / d \mathrm{t}^{2}$ - d. Pitch maneuver, fore and aft test directions. The additional load factor (ΔNx) induced by pitch change, is computed as follows: