Force and surface pressure distributions were measured for a 13% medium speed (NASA MS(1)-0313) airfoil fitted with 20% aileron, 25% slotted flap and 10% slot lip spoiler. All tests were conducted in the Walter Beech Memorial Wind Tunnel at a Reynolds number of 2.2 million and a Mach number of 0.13. Results include lift, drag, pitching moments, control surface normal force and hinge moments, and surface pressure distributions. The basic airfoil exhibits low speed characteristics similar to the GA(W)-2 airfoil. Incremental aileron and spoiler performance are quite comparable to that obtained on the GA(W)-2 airfoil. Slotted flap performance on this section is reduced compared to the GA(W)-2, resulting in a highest c sub l max of 3.00 compared to 3.35 for the GA(W)-2.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind Tunnel Force and Pressure Tests


    Contributors:
    W. H. Wentz (author)

    Publication date :

    1981


    Size :

    114 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Wind tunnel force and pressure tests

    Wentz, W. H., Jr. | NTRS | 1981


    Wind tunnel tests

    Online Contents | 1993


    Wind Tunnel Tests on Wind Pressure Characteristics of Sawtooth Roofs

    Li, Chunguang / Han, Yan / Zhang, Ji et al. | ASCE | 2018


    Unsteady Wind Tunnel Tests

    P. M. Hutin | NTIS | 1992


    Helicopter wind tunnel tests

    Ross, R.S. | Engineering Index Backfile | 1947