EPPLER STF 863-615 AIRFOIL (stf86361-il)
EPPLER STF 863-615 AIRFOIL - Eppler STF 863-615 airfoil
Details | Dat file | Parser | |
(stf86361-il) EPPLER STF 863-615 AIRFOIL Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord. Max camber 4.2% at 72.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
EPPLER STF 863-615 AIRFOIL 33.0 28.0 0.0003200 0.0130400 0.0015800 0.0183800 0.0087300 0.0255100 0.0207500 0.0336300 0.0373800 0.0422900 0.0584600 0.0511700 0.0837300 0.0600300 0.1129700 0.0686600 0.1458600 0.0768700 0.1821000 0.0844900 0.2213200 0.0914000 0.2631200 0.0974400 0.3070800 0.1025300 0.3527600 0.1068500 0.3997100 0.1094400 0.4474300 0.1111200 0.4954800 0.1118700 0.5432700 0.1107300 0.5904100 0.1085900 0.6363600 0.1051400 0.6808600 0.1003400 0.7228000 0.0941700 0.7622600 0.0863200 0.7993300 0.0762200 0.8349100 0.0645300 0.8686900 0.0527200 0.8995800 0.0414500 0.9268900 0.0306700 0.9505600 0.0205100 0.9705100 0.0116700 0.9861600 0.0050400 0.9964000 0.0011900 1.0000000 0.0000000 0.0003200 0.0130400 0.0037000 0.0085000 0.0172900 0.0038200 0.0343700 -.0016100 0.0565800 -.0067200 0.0835900 -.0117000 0.1150300 -.0164600 0.1505000 -.0209000 0.1895600 -.0249300 0.2317400 -.0284700 0.2765200 -.0314200 0.3233700 -.0336800 0.3717400 -.0351500 0.4210400 -.0356900 0.4706700 -.0351200 0.5200300 -.0332100 0.5684100 -.0291500 0.6168200 -.0217100 0.6671600 -.0122300 0.7189100 -.0034400 0.7700700 0.0033600 0.8189700 0.0079400 0.8641800 0.0102000 0.9044800 0.0103400 0.9386100 0.0086800 0.9655900 0.0059100 0.9848100 0.0029900 0.9962300 0.0008100 |
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Polars for EPPLER STF 863-615 AIRFOIL (stf86361-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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stf86361-il | 50,000 | 9 | 22.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
stf86361-il | 50,000 | 5 | 23.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
stf86361-il | 100,000 | 9 | 32.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
stf86361-il | 100,000 | 5 | 34.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
stf86361-il | 200,000 | 9 | 54.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
stf86361-il | 200,000 | 5 | 56.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
stf86361-il | 500,000 | 9 | 92.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
stf86361-il | 500,000 | 5 | 98.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
stf86361-il | 1,000,000 | 9 | 145.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
stf86361-il | 1,000,000 | 5 | 142.7 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |