![]() Wr_35_dataset.txt: airfoil data for the airfoil section located at 35% semispan Wr_30_dataset.txt: airfoil data for the airfoil section located at 30% semispan Wr_25_dataset.txt: airfoil data for the airfoil section located at 25% semispan Wr_20_dataset.txt: airfoil data for the airfoil section located at 20% semispan Wr_15_dataset.txt: airfoil data for the airfoil section located at 15% semispan Wr_10_dataset.txt: airfoil data for the airfoil section located at 10% semispan Wr_0_dataset.txt: airfoil data for the airfoil section located at 0% semispan (wing root) UCRM-9_wr100_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 100% semispan (wing tip) UCRM-9_wr95_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 95% semispan UCRM-9_wr90_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 90% semispan UCRM-9_wr85_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 85% semispan UCRM-9_wr80_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 80% semispan UCRM-9_wr75_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 75% semispan UCRM-9_wr70_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 70% semispan UCRM-9_wr65_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 65% semispan UCRM-9_wr60_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 60% semispan UCRM-9_wr55_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 55% semispan UCRM-9_wr50_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 50% semispan UCRM-9_wr45_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 45% semispan UCRM-9_wr40_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 40% semispan UCRM-9_wr37_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 37% semispan (Yehudi Break) UCRM-9_wr35_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 35% semispan UCRM-9_wr30_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 30% semispan UCRM-9_wr25_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 25% semispan ![]() UCRM-9_wr20_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 20% semispan UCRM-9_wr15_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 15% semispan UCRM-9_wr10_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 10% semispan UCRM-9_wr0_profile.txt: x and y coordinates, normalized by the local wing chord, for the airfoil section located at 0% semispan (wing root) The other 21 files contain airfoil data with the corresponding flap deflection, angle of attack, Reynolds number, and Mach number for each of the 21 airfoil sections (listed above) of the Low-Fidelity Common Research Model. Twenty-one of these files contain the x and y coordinates of the 21 airfoil sections at the spanwise locations listed above (with zero flap deflection). *See for additional details about the data collection process. The data were obtained using the Transonic Small-Disturbance Theory/Integral Boundary layer method from Data were collected for the airfoil sections located at 0, 10, 15, 20, 25, 30, 35, 37, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, and 100% semispan, as a function of flap deflection of a parabolic flap spanning the aft 30% of the chord, angle of attack, Reynolds number, and Mach number. The airfoil database files contain the Lift, Drag, and Moment Coefficient data for the Low-Fidelity Common Research Model wing airfoil sections. Data were extracted from a CAD file of the uCRM-9 wing geometry described in and available at (doi:10.17632/gpk4zn73xn.1) The airfoil profile files contain the x and y coordinates of the airfoil surface, normalized by the local chord for the airfoil sections located at 0, 10, 15, 20, 25, 30, 35, 37, 40, 45, 50, 55, 60, 65, 70, 75, 80, 85, 90, 95, and 100% semispan of the Common Research Model wing.
0 Comments
Leave a Reply. |
AuthorWrite something about yourself. No need to be fancy, just an overview. ArchivesCategories |