DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 50,000 Max Cl/Cd: 31.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df101-il-50000.txt Download as CSV file: xf-df101-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: DF 101 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3896 0.09769 0.09092 -0.0193 1.0000 0.2740
-8.250 -0.4136 0.09624 0.08967 -0.0203 1.0000 0.2798
-8.000 -0.4999 0.07775 0.07146 -0.0418 1.0000 0.1347
-7.750 -0.5279 0.07015 0.06380 -0.0446 1.0000 0.1207
-7.500 -0.5275 0.06630 0.05994 -0.0434 1.0000 0.1187
-7.250 -0.5328 0.06224 0.05584 -0.0423 1.0000 0.1169
-7.000 -0.5404 0.05792 0.05139 -0.0413 1.0000 0.1151
-6.750 -0.5475 0.05329 0.04650 -0.0401 1.0000 0.1132
-6.500 -0.5504 0.04889 0.04174 -0.0387 1.0000 0.1125
-6.250 -0.5473 0.04495 0.03740 -0.0371 1.0000 0.1129
-6.000 -0.5400 0.04121 0.03318 -0.0354 1.0000 0.1137
-5.750 -0.5287 0.03779 0.02921 -0.0337 1.0000 0.1156
-5.500 -0.5151 0.03485 0.02564 -0.0320 1.0000 0.1212
-5.250 -0.4980 0.03304 0.02378 -0.0304 1.0000 0.1304
-5.000 -0.4793 0.03082 0.02130 -0.0288 1.0000 0.1396
-4.750 -0.4609 0.02934 0.01972 -0.0272 1.0000 0.1570
-4.500 -0.4412 0.02771 0.01803 -0.0256 1.0000 0.1805
-4.250 -0.4240 0.02661 0.01714 -0.0236 1.0000 0.2267
-4.000 -0.4093 0.02578 0.01657 -0.0210 1.0000 0.2981
-3.750 -0.3952 0.02538 0.01638 -0.0185 1.0000 0.3584
-3.500 -0.3800 0.02500 0.01615 -0.0161 1.0000 0.4068
-3.250 -0.3629 0.02452 0.01570 -0.0141 1.0000 0.4479
-3.000 -0.3447 0.02399 0.01520 -0.0124 1.0000 0.4828
-2.750 -0.3263 0.02349 0.01465 -0.0108 1.0000 0.5171
-2.500 -0.3071 0.02302 0.01420 -0.0094 1.0000 0.5526
-2.250 -0.2874 0.02258 0.01381 -0.0080 1.0000 0.5936
-2.000 -0.2687 0.02211 0.01351 -0.0064 1.0000 0.6430
-1.750 -0.2523 0.02155 0.01328 -0.0039 1.0000 0.7140
-1.500 -0.1616 0.02089 0.01296 -0.0154 1.0000 1.0000
-1.250 -0.1472 0.02101 0.01260 -0.0152 1.0000 1.0000
-1.000 -0.1314 0.02131 0.01256 -0.0146 1.0000 1.0000
-0.750 -0.1153 0.02168 0.01263 -0.0140 1.0000 1.0000
-0.500 -0.0991 0.02210 0.01281 -0.0133 1.0000 1.0000
-0.250 -0.0828 0.02257 0.01307 -0.0127 1.0000 1.0000
0.000 -0.0665 0.02309 0.01340 -0.0122 1.0000 1.0000
0.250 -0.0501 0.02365 0.01379 -0.0117 1.0000 1.0000
0.500 -0.0201 0.02457 0.01454 -0.0138 0.9948 1.0000
0.750 0.0298 0.02589 0.01568 -0.0196 0.9796 1.0000
1.000 0.0757 0.02706 0.01672 -0.0244 0.9639 1.0000
1.250 0.1201 0.02815 0.01771 -0.0288 0.9476 1.0000
1.500 0.1646 0.02919 0.01866 -0.0330 0.9308 1.0000
1.750 0.2108 0.03016 0.01959 -0.0372 0.9136 1.0000
2.000 0.2525 0.03098 0.02039 -0.0404 0.8956 1.0000
2.250 0.2882 0.03166 0.02106 -0.0424 0.8762 1.0000
2.500 0.3318 0.03226 0.02168 -0.0454 0.8568 1.0000
2.750 0.3837 0.03265 0.02213 -0.0492 0.8380 1.0000
3.000 0.4127 0.03308 0.02261 -0.0494 0.8163 1.0000
3.250 0.4628 0.03310 0.02272 -0.0523 0.7966 1.0000
3.500 0.5050 0.03308 0.02281 -0.0538 0.7758 1.0000
3.750 0.5517 0.03270 0.02256 -0.0554 0.7546 1.0000
4.000 0.6086 0.03162 0.02167 -0.0575 0.7360 1.0000
4.250 0.6375 0.03143 0.02158 -0.0562 0.7119 1.0000
4.500 0.6913 0.02997 0.02028 -0.0570 0.6918 1.0000
4.750 0.7210 0.02957 0.01997 -0.0553 0.6657 1.0000
5.000 0.7547 0.02897 0.01944 -0.0540 0.6394 1.0000
5.250 0.7883 0.02840 0.01891 -0.0525 0.6118 1.0000
5.500 0.8187 0.02811 0.01865 -0.0509 0.5833 1.0000
5.750 0.8464 0.02808 0.01859 -0.0492 0.5545 1.0000
6.000 0.8731 0.02825 0.01871 -0.0476 0.5267 1.0000
6.250 0.8996 0.02853 0.01895 -0.0462 0.5002 1.0000
6.500 0.9191 0.02935 0.01981 -0.0443 0.4749 1.0000
6.750 0.9418 0.03008 0.02052 -0.0428 0.4518 1.0000
7.000 0.9640 0.03093 0.02139 -0.0414 0.4302 1.0000
7.250 0.9874 0.03183 0.02227 -0.0402 0.4102 1.0000
7.500 1.0053 0.03311 0.02372 -0.0386 0.3914 1.0000
7.750 1.0256 0.03431 0.02499 -0.0372 0.3735 1.0000
8.000 1.0467 0.03558 0.02632 -0.0359 0.3567 1.0000
8.250 1.0686 0.03685 0.02763 -0.0347 0.3401 1.0000
8.500 1.0891 0.03833 0.02916 -0.0334 0.3241 1.0000
8.750 1.1036 0.04003 0.03109 -0.0316 0.3085 1.0000
9.000 1.1173 0.04181 0.03306 -0.0297 0.2930 1.0000
9.250 1.1290 0.04363 0.03507 -0.0275 0.2770 1.0000
9.500 1.1397 0.04550 0.03713 -0.0253 0.2607 1.0000
9.750 1.1528 0.04698 0.03869 -0.0232 0.2422 1.0000
10.000 1.1706 0.04806 0.03970 -0.0214 0.2209 1.0000
10.500 1.1907 0.05062 0.04224 -0.0165 0.1791 1.0000
10.750 1.1890 0.05280 0.04460 -0.0133 0.1640 1.0000
11.000 1.1891 0.05499 0.04688 -0.0104 0.1501 1.0000
11.250 0.9182 0.08952 0.08228 -0.0184 0.2407 1.0000
11.500 0.8937 0.09861 0.09129 -0.0223 0.2385 1.0000
11.750 0.8721 0.10742 0.10003 -0.0260 0.2378 1.0000
12.000 0.8540 0.11560 0.10817 -0.0295 0.2375 1.0000
12.250 0.8400 0.12318 0.11573 -0.0326 0.2373 1.0000
12.500 1.0357 0.08369 0.07693 -0.0009 0.1403 1.0000
12.750 1.0146 0.09033 0.08361 -0.0029 0.1390 1.0000
13.000 0.5833 0.14530 0.13807 -0.0426 0.3472 1.0000
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Polar data table (+)
Polar graphs
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