DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 200,000 Max Cl/Cd: 63.04 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-df101-il-200000-n5.txt Download as CSV file: xf-df101-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5735 0.07566 0.07190 -0.0429 1.0000 0.0114
-11.000 -0.5947 0.06709 0.06329 -0.0487 1.0000 0.0112
-10.750 -0.6140 0.05890 0.05501 -0.0554 1.0000 0.0111
-10.500 -0.6348 0.05144 0.04740 -0.0626 1.0000 0.0110
-10.250 -0.6541 0.04709 0.04291 -0.0650 1.0000 0.0109
-10.000 -0.6753 0.04426 0.03992 -0.0628 1.0000 0.0109
-9.750 -0.6907 0.04142 0.03687 -0.0600 1.0000 0.0109
-9.500 -0.7029 0.03866 0.03384 -0.0568 1.0000 0.0110
-9.250 -0.7098 0.03633 0.03125 -0.0533 1.0000 0.0110
-9.000 -0.7154 0.03394 0.02852 -0.0496 1.0000 0.0112
-8.750 -0.7156 0.03192 0.02617 -0.0462 1.0000 0.0113
-8.500 -0.6918 0.02922 0.02314 -0.0476 0.9953 0.0116
-8.250 -0.6662 0.02736 0.02107 -0.0487 0.9906 0.0120
-8.000 -0.6377 0.02609 0.01963 -0.0500 0.9862 0.0128
-7.750 -0.6072 0.02473 0.01804 -0.0515 0.9828 0.0139
-7.500 -0.5806 0.02336 0.01640 -0.0518 0.9774 0.0149
-7.250 -0.5513 0.02185 0.01468 -0.0527 0.9733 0.0156
-7.000 -0.5203 0.02047 0.01321 -0.0541 0.9703 0.0165
-6.750 -0.4936 0.01949 0.01216 -0.0543 0.9645 0.0176
-6.500 -0.4631 0.01853 0.01107 -0.0552 0.9602 0.0191
-6.250 -0.4311 0.01758 0.01002 -0.0565 0.9568 0.0213
-6.000 -0.4041 0.01693 0.00930 -0.0566 0.9505 0.0242
-5.750 -0.3743 0.01619 0.00844 -0.0572 0.9454 0.0272
-5.500 -0.3419 0.01549 0.00768 -0.0583 0.9417 0.0320
-5.250 -0.3170 0.01492 0.00707 -0.0578 0.9340 0.0387
-5.000 -0.2868 0.01429 0.00642 -0.0584 0.9289 0.0515
-4.750 -0.2608 0.01359 0.00588 -0.0582 0.9221 0.0832
-4.500 -0.2337 0.01298 0.00550 -0.0583 0.9155 0.1383
-4.250 -0.2054 0.01264 0.00523 -0.0584 0.9093 0.1737
-4.000 -0.1783 0.01238 0.00499 -0.0582 0.9017 0.2003
-3.750 -0.1499 0.01213 0.00480 -0.0583 0.8953 0.2324
-3.500 -0.1237 0.01192 0.00465 -0.0579 0.8869 0.2635
-3.250 -0.0962 0.01170 0.00445 -0.0577 0.8797 0.2840
-3.000 -0.0695 0.01151 0.00424 -0.0573 0.8711 0.3004
-2.750 -0.0426 0.01133 0.00406 -0.0570 0.8628 0.3176
-2.500 -0.0154 0.01114 0.00387 -0.0567 0.8545 0.3366
-2.250 0.0106 0.01097 0.00371 -0.0562 0.8449 0.3568
-2.000 0.0375 0.01077 0.00355 -0.0558 0.8362 0.3812
-1.750 0.0634 0.01058 0.00342 -0.0552 0.8262 0.4094
-1.500 0.0891 0.01038 0.00332 -0.0547 0.8159 0.4446
-1.250 0.1146 0.01016 0.00321 -0.0540 0.8058 0.4884
-1.000 0.1396 0.00992 0.00312 -0.0532 0.7951 0.5420
-0.750 0.1638 0.00969 0.00307 -0.0522 0.7832 0.6028
-0.500 0.1878 0.00946 0.00303 -0.0511 0.7712 0.6675
-0.250 0.2121 0.00923 0.00301 -0.0499 0.7585 0.7393
0.000 0.2414 0.00907 0.00306 -0.0494 0.7449 0.8250
0.250 0.2814 0.00908 0.00309 -0.0513 0.7289 0.8927
0.500 0.3191 0.00913 0.00306 -0.0529 0.7112 0.9292
0.750 0.3560 0.00921 0.00303 -0.0545 0.6937 0.9523
1.000 0.3924 0.00930 0.00302 -0.0561 0.6770 0.9694
1.250 0.4319 0.00939 0.00301 -0.0585 0.6596 0.9819
1.500 0.4718 0.00947 0.00300 -0.0610 0.6416 0.9922
1.750 0.5083 0.00956 0.00300 -0.0629 0.6233 1.0000
2.000 0.5309 0.00968 0.00303 -0.0618 0.6065 1.0000
2.250 0.5534 0.00982 0.00309 -0.0607 0.5889 1.0000
2.500 0.5759 0.00997 0.00316 -0.0596 0.5709 1.0000
2.750 0.5983 0.01013 0.00325 -0.0585 0.5514 1.0000
3.000 0.6204 0.01031 0.00334 -0.0573 0.5312 1.0000
3.250 0.6424 0.01050 0.00347 -0.0561 0.5102 1.0000
3.500 0.6642 0.01072 0.00360 -0.0549 0.4876 1.0000
3.750 0.6857 0.01096 0.00375 -0.0536 0.4633 1.0000
4.000 0.7068 0.01123 0.00393 -0.0523 0.4374 1.0000
4.250 0.7275 0.01154 0.00412 -0.0510 0.4110 1.0000
4.500 0.7480 0.01187 0.00434 -0.0496 0.3838 1.0000
4.750 0.7684 0.01222 0.00459 -0.0482 0.3576 1.0000
5.000 0.7890 0.01259 0.00488 -0.0469 0.3340 1.0000
5.250 0.8095 0.01297 0.00517 -0.0456 0.3119 1.0000
5.500 0.8303 0.01336 0.00549 -0.0444 0.2927 1.0000
5.750 0.8513 0.01374 0.00582 -0.0432 0.2755 1.0000
6.000 0.8723 0.01413 0.00619 -0.0421 0.2598 1.0000
6.250 0.8935 0.01452 0.00655 -0.0410 0.2462 1.0000
6.500 0.9145 0.01492 0.00694 -0.0399 0.2339 1.0000
6.750 0.9352 0.01535 0.00734 -0.0387 0.2224 1.0000
7.000 0.9566 0.01574 0.00776 -0.0377 0.2117 1.0000
7.250 0.9776 0.01615 0.00821 -0.0366 0.2017 1.0000
7.500 0.9980 0.01660 0.00867 -0.0354 0.1920 1.0000
7.750 1.0184 0.01704 0.00913 -0.0343 0.1821 1.0000
8.000 1.0388 0.01747 0.00961 -0.0331 0.1718 1.0000
8.250 1.0583 0.01794 0.01009 -0.0319 0.1600 1.0000
8.500 1.0772 0.01844 0.01060 -0.0306 0.1455 1.0000
8.750 1.0951 0.01899 0.01110 -0.0293 0.1294 1.0000
9.000 1.1128 0.01956 0.01167 -0.0279 0.1162 1.0000
9.250 1.1297 0.02016 0.01227 -0.0264 0.1035 1.0000
9.500 1.1453 0.02083 0.01293 -0.0247 0.0900 1.0000
9.750 1.1585 0.02157 0.01366 -0.0227 0.0769 1.0000
10.000 1.1697 0.02242 0.01448 -0.0204 0.0636 1.0000
10.250 1.1795 0.02338 0.01541 -0.0180 0.0506 1.0000
10.500 1.1876 0.02449 0.01649 -0.0156 0.0400 1.0000
10.750 1.1945 0.02571 0.01771 -0.0132 0.0327 1.0000
11.000 1.2024 0.02686 0.01894 -0.0110 0.0285 1.0000
11.250 1.2073 0.02827 0.02039 -0.0088 0.0252 1.0000
11.500 1.2143 0.02955 0.02180 -0.0068 0.0232 1.0000
11.750 1.2191 0.03103 0.02342 -0.0049 0.0217 1.0000
12.000 1.2219 0.03272 0.02521 -0.0031 0.0205 1.0000
12.250 1.2210 0.03479 0.02739 -0.0014 0.0196 1.0000
12.500 1.2222 0.03678 0.02951 0.0000 0.0191 1.0000
12.750 1.2235 0.03890 0.03178 0.0010 0.0185 1.0000
13.000 1.2232 0.04127 0.03430 0.0019 0.0179 1.0000
13.250 1.2225 0.04382 0.03698 0.0024 0.0172 1.0000
13.500 1.2206 0.04661 0.03992 0.0027 0.0168 1.0000
13.750 1.2177 0.04966 0.04309 0.0026 0.0163 1.0000
14.000 1.2145 0.05290 0.04646 0.0022 0.0159 1.0000
14.250 1.2088 0.05659 0.05027 0.0015 0.0155 1.0000
14.500 1.2009 0.06074 0.05453 0.0005 0.0151 1.0000
14.750 1.1920 0.06522 0.05912 -0.0009 0.0148 1.0000
15.000 1.1833 0.06981 0.06381 -0.0023 0.0146 1.0000
15.250 1.1778 0.07416 0.06830 -0.0039 0.0145 1.0000
15.500 1.1713 0.07883 0.07317 -0.0057 0.0142 1.0000
15.750 1.1643 0.08371 0.07820 -0.0077 0.0141 1.0000
16.000 1.1576 0.08870 0.08332 -0.0099 0.0139 1.0000
16.250 1.1502 0.09391 0.08868 -0.0122 0.0138 1.0000
16.500 1.1426 0.09927 0.09419 -0.0147 0.0136 1.0000
16.750 1.1349 0.10478 0.09984 -0.0174 0.0135 1.0000
17.000 1.1263 0.11063 0.10584 -0.0203 0.0133 1.0000
17.250 1.1175 0.11664 0.11199 -0.0235 0.0132 1.0000
17.500 1.1084 0.12285 0.11834 -0.0268 0.0130 1.0000
17.750 1.0991 0.12930 0.12493 -0.0305 0.0129 1.0000
18.000 1.0887 0.13615 0.13192 -0.0344 0.0127 1.0000
18.250 1.0782 0.14311 0.13902 -0.0384 0.0127 1.0000
18.500 1.0664 0.15065 0.14669 -0.0429 0.0126 1.0000
18.750 1.0525 0.15901 0.15519 -0.0479 0.0125 1.0000
19.000 1.0337 0.16915 0.16549 -0.0540 0.0126 1.0000
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