(Dicke 12.28%) (e171-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: (Dicke 12.28%) (e171-il) Reynolds number: 100,000 Max Cl/Cd: 43.55 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e171-il-100000.txt Download as CSV file: xf-e171-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.5643 0.10508 0.10057 -0.0134 1.0000 0.0731
-11.750 -0.6654 0.10392 0.09906 -0.0112 1.0000 0.0664
-11.500 -0.7489 0.08281 0.07783 -0.0292 1.0000 0.0577
-11.250 -0.7645 0.07689 0.07186 -0.0316 1.0000 0.0566
-11.000 -0.7830 0.07174 0.06663 -0.0337 1.0000 0.0556
-10.750 -0.8059 0.06695 0.06169 -0.0347 1.0000 0.0547
-10.500 -0.8274 0.06282 0.05741 -0.0342 1.0000 0.0536
-10.250 -0.8494 0.05907 0.05344 -0.0318 1.0000 0.0524
-10.000 -0.8714 0.05460 0.04857 -0.0290 1.0000 0.0506
-9.750 -0.8916 0.05044 0.04372 -0.0251 1.0000 0.0483
-9.500 -0.8894 0.04736 0.04014 -0.0226 1.0000 0.0477
-9.250 -0.8826 0.04398 0.03637 -0.0206 1.0000 0.0476
-9.000 -0.8721 0.04005 0.03211 -0.0190 1.0000 0.0482
-8.750 -0.8569 0.03740 0.02938 -0.0180 1.0000 0.0510
-8.500 -0.8403 0.03524 0.02701 -0.0166 1.0000 0.0541
-8.250 -0.8216 0.03276 0.02416 -0.0151 1.0000 0.0564
-8.000 -0.8007 0.03071 0.02173 -0.0136 1.0000 0.0590
-7.750 -0.7786 0.02823 0.01938 -0.0131 1.0000 0.0658
-7.500 -0.7561 0.02642 0.01736 -0.0119 1.0000 0.0722
-7.250 -0.7367 0.02473 0.01579 -0.0106 1.0000 0.0822
-7.000 -0.7200 0.02313 0.01428 -0.0088 1.0000 0.0960
-6.750 -0.7083 0.02143 0.01284 -0.0063 1.0000 0.1172
-6.500 -0.7005 0.01970 0.01150 -0.0033 1.0000 0.1588
-6.250 -0.6964 0.01788 0.01029 0.0002 1.0000 0.2333
-6.000 -0.6922 0.01639 0.00951 0.0037 1.0000 0.3351
-5.750 -0.6837 0.01570 0.00937 0.0072 1.0000 0.4358
-5.500 -0.6704 0.01568 0.00950 0.0103 1.0000 0.5008
-5.250 -0.6554 0.01585 0.00967 0.0132 1.0000 0.5431
-5.000 -0.6406 0.01605 0.00984 0.0160 1.0000 0.5743
-4.750 -0.6265 0.01627 0.01004 0.0189 1.0000 0.5997
-4.500 -0.6143 0.01644 0.01014 0.0218 1.0000 0.6230
-4.250 -0.6008 0.01668 0.01039 0.0247 1.0000 0.6420
-4.000 -0.5881 0.01687 0.01052 0.0273 1.0000 0.6604
-3.750 -0.5752 0.01702 0.01060 0.0298 1.0000 0.6784
-3.500 -0.5448 0.01731 0.01083 0.0291 0.9944 0.6970
-3.250 -0.5014 0.01764 0.01108 0.0263 0.9842 0.7152
-3.000 -0.4606 0.01784 0.01117 0.0239 0.9735 0.7319
-2.750 -0.4206 0.01797 0.01122 0.0216 0.9634 0.7475
-2.500 -0.3758 0.01809 0.01123 0.0184 0.9554 0.7618
-2.250 -0.3385 0.01810 0.01118 0.0166 0.9448 0.7745
-2.000 -0.2990 0.01809 0.01110 0.0143 0.9358 0.7867
-1.750 -0.2543 0.01805 0.01097 0.0110 0.9286 0.7987
-1.500 -0.2191 0.01800 0.01087 0.0095 0.9187 0.8101
-1.250 -0.1719 0.01799 0.01083 0.0062 0.9128 0.8190
-1.000 -0.1403 0.01792 0.01072 0.0053 0.9021 0.8292
-0.750 -0.1072 0.01783 0.01059 0.0042 0.8929 0.8401
-0.500 -0.0652 0.01783 0.01058 0.0018 0.8853 0.8476
-0.250 -0.0356 0.01781 0.01054 0.0014 0.8750 0.8575
0.000 0.0000 0.01777 0.01049 0.0000 0.8670 0.8669
0.250 0.0356 0.01781 0.01054 -0.0014 0.8575 0.8751
0.500 0.0652 0.01783 0.01058 -0.0018 0.8475 0.8853
0.750 0.1072 0.01783 0.01059 -0.0041 0.8401 0.8929
1.000 0.1402 0.01792 0.01072 -0.0053 0.8292 0.9021
1.250 0.1719 0.01799 0.01082 -0.0062 0.8190 0.9128
1.500 0.2191 0.01800 0.01087 -0.0095 0.8103 0.9187
1.750 0.2543 0.01805 0.01097 -0.0110 0.7987 0.9286
2.000 0.2989 0.01809 0.01110 -0.0143 0.7867 0.9359
2.250 0.3385 0.01810 0.01117 -0.0166 0.7745 0.9449
2.500 0.3757 0.01808 0.01122 -0.0184 0.7617 0.9554
2.750 0.4205 0.01797 0.01122 -0.0216 0.7474 0.9634
3.000 0.4606 0.01784 0.01117 -0.0239 0.7319 0.9736
3.250 0.5014 0.01763 0.01107 -0.0263 0.7151 0.9842
3.500 0.5449 0.01731 0.01082 -0.0291 0.6970 0.9945
3.750 0.5751 0.01702 0.01060 -0.0298 0.6785 1.0000
4.000 0.5879 0.01687 0.01052 -0.0273 0.6606 1.0000
4.250 0.6007 0.01668 0.01039 -0.0247 0.6420 1.0000
4.500 0.6142 0.01644 0.01014 -0.0218 0.6230 1.0000
4.750 0.6264 0.01626 0.01003 -0.0189 0.5997 1.0000
5.000 0.6405 0.01605 0.00984 -0.0160 0.5744 1.0000
5.250 0.6553 0.01584 0.00967 -0.0132 0.5431 1.0000
5.500 0.6703 0.01568 0.00950 -0.0103 0.5009 1.0000
5.750 0.6837 0.01570 0.00937 -0.0072 0.4360 1.0000
6.000 0.6921 0.01639 0.00951 -0.0037 0.3348 1.0000
6.250 0.6964 0.01788 0.01029 -0.0002 0.2334 1.0000
6.500 0.7005 0.01970 0.01150 0.0033 0.1588 1.0000
6.750 0.7082 0.02144 0.01284 0.0063 0.1170 1.0000
7.000 0.7200 0.02313 0.01428 0.0088 0.0959 1.0000
7.250 0.7367 0.02473 0.01578 0.0106 0.0822 1.0000
7.500 0.7561 0.02643 0.01736 0.0119 0.0722 1.0000
7.750 0.7786 0.02823 0.01939 0.0131 0.0656 1.0000
8.000 0.8008 0.03071 0.02172 0.0136 0.0590 1.0000
8.250 0.8218 0.03276 0.02415 0.0151 0.0565 1.0000
8.500 0.8404 0.03524 0.02700 0.0166 0.0541 1.0000
8.750 0.8568 0.03745 0.02944 0.0180 0.0511 1.0000
9.000 0.8722 0.04003 0.03209 0.0190 0.0483 1.0000
9.250 0.8828 0.04395 0.03633 0.0205 0.0476 1.0000
9.500 0.8894 0.04743 0.04021 0.0226 0.0476 1.0000
9.750 0.8919 0.05038 0.04361 0.0251 0.0483 1.0000
10.000 0.8711 0.05466 0.04863 0.0290 0.0506 1.0000
10.250 0.8501 0.05906 0.05343 0.0317 0.0525 1.0000
10.500 0.8270 0.06291 0.05750 0.0341 0.0536 1.0000
10.750 0.8064 0.06703 0.06178 0.0346 0.0548 1.0000
11.000 0.7830 0.07183 0.06671 0.0336 0.0556 1.0000
11.250 0.7626 0.07718 0.07216 0.0313 0.0565 1.0000
11.500 0.7517 0.08276 0.07776 0.0294 0.0578 1.0000
11.750 0.6655 0.10419 0.09933 0.0110 0.0664 1.0000
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Polar data table (+)
Polar graphs
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