S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) - Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane.
| Details | Dat file | Parser | |
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(s4096-il) S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) Selig airfoil for micro RC soaring. Used on the E-flite UMX ASK-21 scale RC sailplane. Max thickness 12.5% at 34% chord. Max camber 1.2% at 34% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane)
1.001130281960000000 0.031254596379819470
0.997680476976490600 0.031382924998537240
0.987882459888131900 0.032269529839729920
0.972575261447100900 0.034120140575423060
0.951995774051603800 0.036476509688507750
0.926226415549459100 0.039288486420531950
0.895619627068446700 0.042593978527484340
0.860619236097899300 0.046360569862312630
0.821706666904956200 0.050520609841309620
0.779399916227590500 0.054974673821538240
0.734250252844644600 0.059615365255700450
0.686832648139053200 0.064310850942797360
0.637740433695872000 0.068918589738607010
0.587576379975584200 0.073275191744158030
0.536946910384709800 0.077201723093683600
0.486463523127371700 0.080482186096370290
0.436596772391310500 0.082785692106651400
0.387681900257797800 0.083975783663870500
0.340127862135722000 0.084057743210041980
0.294386216166903300 0.082994105184726910
0.250874819457253600 0.080752392202059760
0.209973835634555600 0.077327948602564370
0.172031076403795700 0.072733911762463940
0.137348580423802400 0.067019954896448620
0.106193958646291600 0.060257643737809180
0.078781258739159310 0.052562302034780830
0.055293282158342950 0.044076349216846040
0.035851604062848710 0.034996427359354940
0.020561549284058290 0.025561336259403480
0.009464552300117557 0.016089981807731260
0.002639731336090301 0.006974640837649897
0.000061276786812114 -0.001051083751989839
0.003089616767258052 -0.007519266442942546
0.012385517294676300 -0.013251171895737490
0.026989587875609570 -0.018736253731722240
0.046689514727003110 -0.023732371451779660
0.071286355693549020 -0.028149255660321280
0.100543245434217000 -0.031948497618370850
0.134165126283259400 -0.035099126460409210
0.171810001030032100 -0.037584520728885170
0.213077777969174400 -0.039379773970220310
0.257627015555636100 -0.040390492851046040
0.305160773894100600 -0.040712438225610680
0.355191458236692100 -0.040608105836720780
0.407084805700655000 -0.040196243796381910
0.460206249491688500 -0.039555751959305220
0.513914628376883800 -0.038750923106367060
0.567567387301825800 -0.037833398803049490
0.620526032891672200 -0.036851255057360990
0.672161601981521500 -0.035845602201291170
0.721860272195737600 -0.034856135912581110
0.769028683078998500 -0.033917456458915870
0.813099190469908000 -0.033061112717391770
0.853534774357230400 -0.032314270721741050
0.889833386145347800 -0.031694355774974320
0.921532324476128300 -0.031217737651448470
0.948201132323621300 -0.030848465444363700
0.969568434028279200 -0.030535420867795610
0.985452131737802600 -0.030404511438444450
0.995462383821124400 -0.030702642390694940
0.998929073543581000 -0.030982385892783910
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Polars for S4096 (designed for the E-flite UMX ASK-21 scale RC sailplane) (s4096-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4096-il | 50,000 | 9 | 27.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 50,000 | 5 | 31.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 100,000 | 9 | 39.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 100,000 | 5 | 40.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 200,000 | 9 | 49 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 200,000 | 5 | 48.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 500,000 | 9 | 59.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 500,000 | 5 | 57.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4096-il | 1,000,000 | 9 | 65.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4096-il | 1,000,000 | 5 | 63.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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