(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 50,000 Max Cl/Cd: 29.34 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e171-il-50000-n5.txt Download as CSV file: xf-e171-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: (Dicke 12.28%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6914 0.10148 0.09456 -0.0140 1.0000 0.0419
-12.000 -0.7157 0.09194 0.08499 -0.0202 1.0000 0.0411
-11.750 -0.7409 0.08376 0.07673 -0.0255 1.0000 0.0403
-11.500 -0.7668 0.07669 0.06950 -0.0297 1.0000 0.0397
-11.250 -0.7890 0.07103 0.06367 -0.0324 1.0000 0.0393
-11.000 -0.8079 0.06629 0.05872 -0.0336 1.0000 0.0392
-10.750 -0.8232 0.06225 0.05446 -0.0336 1.0000 0.0393
-10.500 -0.8348 0.05872 0.05068 -0.0327 1.0000 0.0396
-10.250 -0.8427 0.05551 0.04721 -0.0309 1.0000 0.0401
-10.000 -0.8456 0.05241 0.04382 -0.0291 1.0000 0.0411
-9.750 -0.8440 0.04954 0.04060 -0.0275 1.0000 0.0432
-9.500 -0.8397 0.04675 0.03730 -0.0257 1.0000 0.0458
-9.250 -0.8269 0.04409 0.03456 -0.0247 1.0000 0.0490
-9.000 -0.8098 0.04170 0.03192 -0.0237 1.0000 0.0520
-8.750 -0.7876 0.03929 0.02918 -0.0227 1.0000 0.0562
-8.500 -0.7703 0.03740 0.02725 -0.0217 1.0000 0.0624
-8.250 -0.7505 0.03570 0.02528 -0.0205 1.0000 0.0705
-8.000 -0.7338 0.03392 0.02358 -0.0191 1.0000 0.0777
-7.750 -0.7202 0.03229 0.02191 -0.0174 1.0000 0.0889
-7.500 -0.7092 0.03072 0.02039 -0.0155 1.0000 0.1050
-7.250 -0.6997 0.02911 0.01888 -0.0134 1.0000 0.1261
-7.000 -0.6919 0.02747 0.01743 -0.0112 1.0000 0.1564
-6.750 -0.6851 0.02585 0.01613 -0.0088 1.0000 0.2003
-6.500 -0.6784 0.02435 0.01502 -0.0063 1.0000 0.2573
-6.250 -0.6706 0.02315 0.01427 -0.0034 1.0000 0.3254
-6.000 -0.6599 0.02249 0.01401 -0.0003 1.0000 0.3973
-5.750 -0.6466 0.02226 0.01393 0.0027 1.0000 0.4579
-5.500 -0.6317 0.02223 0.01390 0.0056 1.0000 0.5034
-5.250 -0.6162 0.02225 0.01385 0.0083 1.0000 0.5389
-5.000 -0.6004 0.02226 0.01371 0.0110 1.0000 0.5682
-4.750 -0.5838 0.02230 0.01366 0.0136 1.0000 0.5927
-4.500 -0.5689 0.02225 0.01349 0.0161 1.0000 0.6152
-4.250 -0.5527 0.02227 0.01344 0.0187 1.0000 0.6342
-4.000 -0.5387 0.02221 0.01329 0.0212 1.0000 0.6524
-3.750 -0.5262 0.02212 0.01308 0.0238 1.0000 0.6699
-3.500 -0.5132 0.02205 0.01293 0.0263 1.0000 0.6857
-3.250 -0.4802 0.02213 0.01281 0.0252 0.9901 0.7019
-3.000 -0.4420 0.02217 0.01270 0.0231 0.9772 0.7173
-2.750 -0.4042 0.02217 0.01254 0.0210 0.9648 0.7316
-2.500 -0.3656 0.02214 0.01233 0.0186 0.9532 0.7451
-2.250 -0.3269 0.02208 0.01213 0.0163 0.9421 0.7579
-2.000 -0.2897 0.02200 0.01193 0.0142 0.9308 0.7698
-1.750 -0.2498 0.02196 0.01178 0.0118 0.9208 0.7799
-1.500 -0.2100 0.02188 0.01161 0.0093 0.9115 0.7901
-1.250 -0.1749 0.02178 0.01144 0.0076 0.9006 0.8008
-1.000 -0.1400 0.02173 0.01131 0.0061 0.8897 0.8108
-0.750 -0.1030 0.02169 0.01123 0.0042 0.8800 0.8200
-0.500 -0.0669 0.02162 0.01113 0.0025 0.8706 0.8301
-0.250 -0.0358 0.02160 0.01108 0.0016 0.8595 0.8406
0.000 0.0000 0.02161 0.01110 0.0000 0.8496 0.8496
0.250 0.0358 0.02160 0.01108 -0.0016 0.8407 0.8595
0.500 0.0669 0.02162 0.01113 -0.0025 0.8301 0.8706
0.750 0.1030 0.02169 0.01123 -0.0042 0.8200 0.8800
1.000 0.1400 0.02172 0.01131 -0.0061 0.8108 0.8897
1.250 0.1748 0.02178 0.01144 -0.0076 0.8008 0.9006
1.500 0.2099 0.02188 0.01161 -0.0093 0.7901 0.9116
1.750 0.2497 0.02196 0.01178 -0.0118 0.7799 0.9208
2.000 0.2896 0.02199 0.01193 -0.0142 0.7699 0.9308
2.250 0.3269 0.02207 0.01213 -0.0163 0.7579 0.9422
2.500 0.3655 0.02214 0.01233 -0.0186 0.7452 0.9533
2.750 0.4041 0.02217 0.01254 -0.0209 0.7317 0.9649
3.000 0.4420 0.02217 0.01269 -0.0231 0.7173 0.9774
3.250 0.4802 0.02212 0.01281 -0.0252 0.7019 0.9902
3.500 0.5129 0.02205 0.01293 -0.0263 0.6858 1.0000
3.750 0.5259 0.02211 0.01308 -0.0238 0.6700 1.0000
4.000 0.5384 0.02221 0.01328 -0.0212 0.6524 1.0000
4.250 0.5524 0.02227 0.01344 -0.0186 0.6342 1.0000
4.500 0.5687 0.02224 0.01349 -0.0161 0.6152 1.0000
4.750 0.5836 0.02230 0.01366 -0.0135 0.5927 1.0000
5.000 0.6002 0.02226 0.01370 -0.0110 0.5682 1.0000
5.250 0.6160 0.02225 0.01384 -0.0083 0.5389 1.0000
5.500 0.6316 0.02223 0.01391 -0.0055 0.5035 1.0000
5.750 0.6464 0.02226 0.01393 -0.0026 0.4578 1.0000
6.000 0.6598 0.02249 0.01401 0.0004 0.3975 1.0000
6.250 0.6706 0.02314 0.01427 0.0034 0.3254 1.0000
6.500 0.6784 0.02435 0.01502 0.0063 0.2572 1.0000
6.750 0.6852 0.02585 0.01613 0.0088 0.2003 1.0000
7.000 0.6921 0.02747 0.01743 0.0112 0.1565 1.0000
7.250 0.6998 0.02911 0.01889 0.0134 0.1260 1.0000
7.500 0.7095 0.03073 0.02040 0.0154 0.1048 1.0000
7.750 0.7204 0.03230 0.02192 0.0173 0.0886 1.0000
8.000 0.7343 0.03392 0.02357 0.0190 0.0779 1.0000
8.250 0.7511 0.03571 0.02527 0.0204 0.0706 1.0000
8.500 0.7710 0.03741 0.02726 0.0216 0.0624 1.0000
8.750 0.7883 0.03931 0.02920 0.0226 0.0562 1.0000
9.000 0.8104 0.04171 0.03194 0.0236 0.0520 1.0000
9.250 0.8273 0.04411 0.03457 0.0246 0.0488 1.0000
9.500 0.8401 0.04677 0.03733 0.0256 0.0458 1.0000
9.750 0.8447 0.04955 0.04061 0.0273 0.0432 1.0000
10.000 0.8463 0.05245 0.04386 0.0290 0.0411 1.0000
10.250 0.8435 0.05555 0.04726 0.0308 0.0402 1.0000
10.500 0.8354 0.05880 0.05077 0.0325 0.0396 1.0000
10.750 0.8238 0.06233 0.05453 0.0335 0.0393 1.0000
11.000 0.8086 0.06636 0.05879 0.0334 0.0392 1.0000
11.250 0.7896 0.07112 0.06375 0.0322 0.0392 1.0000
11.500 0.7668 0.07690 0.06973 0.0295 0.0396 1.0000
11.750 0.7421 0.08380 0.07676 0.0253 0.0402 1.0000
12.000 0.7146 0.09247 0.08553 0.0196 0.0409 1.0000
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Polar data table (+)
Polar graphs
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