AS5048 (18%) (as5048-il)
AS5048 (18%) - AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil
| Details | Dat file | Parser | |
|
(as5048-il) AS5048 (18%) AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil Max thickness 18% at 38.3% chord. Max camber 0.8% at 77.8% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
AS5048 (18%) 1.0000 .00150 .99795 .00261 .99261 .00526 .98429 .00834 .97271 .01198 .95837 .01595 .94112 .01990 .92072 .02396 .89732 .02822 .87111 .03280 .84231 .03773 .81114 .04314 .77793 .04906 .74304 .05563 .70708 .06281 .67063 .07045 .63428 .07812 .59851 .08492 .56284 .09044 .52688 .09468 .49071 .09776 .45445 .09986 .41832 .10106 .38251 .10140 .34725 .10094 .31275 .09972 .27924 .09776 .24695 .09505 .21603 .09161 .18663 .08747 .15891 .08271 .13309 .07739 .10936 .07152 .08785 .06502 .06852 .05792 .05146 .05041 .03674 .04254 .02438 .03444 .01454 .02625 .00721 .01805 .00240 .01003 .00014 .00239 .00041 -.00424 .00441 -.00990 .01248 -.01556 .02377 -.02150 .03798 -.02765 .05482 -.03390 .07412 -.04008 .09574 -.04606 .11951 -.05174 .14532 -.05699 .17306 -.06177 .20256 -.06603 .23366 -.06976 .26613 -.07290 .29980 -.07540 .33444 -.07722 .36986 -.07831 .40583 -.07864 .44212 -.07817 .47846 -.07674 .51476 -.07422 .55088 -.07046 .58702 -.06529 .62334 -.05893 .65996 -.05165 .69717 -.04405 .73423 -.03698 .77029 -.03077 .80489 -.02531 .83759 -.02055 .86800 -.01650 .89575 -.01309 .92048 -.01021 .94185 -.00763 .96018 -.00471 .97608 -.00204 .98886 -.00090 .99713 -.00109 1.0000 -.00149 http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/ |
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for AS5048 (18%) (as5048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| as5048-il | 50,000 | 9 | 25 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 50,000 | 5 | 23.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 9 | 41.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 100,000 | 5 | 40.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 9 | 59.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 200,000 | 5 | 56.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 9 | 81.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 500,000 | 5 | 71 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 9 | 96.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| as5048-il | 1,000,000 | 5 | 79.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||