| タイトル | The Development of Cambered Airfoil Sections Having Favorable Lift Characteristics at Supercritical Mach Numbers |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930082444 |
| 著者（英） | Graham, Donald J |
| 著者所属（英） | National Advisory Committee for Aeronautics. Ames Aeronautical Lab. |
| 発行日 | 1948-12-01 |
| 言語 | eng |
| 内容記述 | Several groups of new airfoil sections, designated as the NACA 8-series, are derived analytically to have lift characteristics at supercritical Mach numbers which are favorable in the sense that the abrupt loss of lift, characteristic of the usual airfoil section at Mach numbers above the critical, is avoided. Aerodynamic characteristics determined, from two-dimensional windtunnel tests at Mach numbers up to approximately 0.9 are presented for each of the derived airfoils. Comparisons are made between the characteristics of these airfoils and the corresponding characteristics of representative NPiCA 6-series airfoils. The experimental results confirm the design expectations in demonstrating for the NACA S-series airfoils either no variation, or an Increase from the low-speed design value, In the lift coefficient at a constant angle of attack with increasing Mach number above the critical. It was not found possible to improve the variation with Mach number of the slope of the lift curve for these airfoils above that for the NACA 6-series airfoils. The drag characteristics of the new airfoils are somewhat inferior to those of the NACA 6- series with respect to divergence with Mach number, but the pitching-moment characteristics are more favorable for the thinner new sections In demonstrating somewhat smaller variations of moment coefficient with both angle of attack and Mach number. The effect on the aero&ynamic characteristics at high Mach numbers of removing the cusp from the trailing-edge regions of two 10-percent-chord-thick NACA 6-series airfoils is determined to be negligible. |
| NASA分類 | Aircraft Stability and Control |
| レポートNO | 93R11734
NACA-TN-1771 |
| 権利 | No Copyright |
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