| Popis: |
A method is presented for the determination of airplane performance by use of formulas and charts. The conventional method of approximating a polar by expressing the effective induced drag as Ci/7rA.R.e is often inadequate because of the fact that many polars are not symmetrical about zero lift. A mathematical expression for the airplane polar is determined here by expressing the effective induced drag as a parabola symmetrical about the lift coefficient at which the minimum drag coefficient occurs. This coefficient is defined as CLmin. The minimum drag coefficient is defkied as Cj)m Hence, the airplane drag coefficient is |
