DF 101 AIRFOIL (df101-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DF 101 AIRFOIL (df101-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.43 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-df101-il-1000000.txt Download as CSV file: xf-df101-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.7917 0.04573 0.04330 -0.0635 1.0000 0.0058
-12.000 -0.7997 0.04025 0.03766 -0.0691 1.0000 0.0058
-11.750 -0.8164 0.03603 0.03328 -0.0713 1.0000 0.0058
-11.500 -0.8391 0.03319 0.03028 -0.0685 1.0000 0.0059
-11.250 -0.8506 0.03122 0.02815 -0.0646 1.0000 0.0058
-11.000 -0.8575 0.02919 0.02594 -0.0611 1.0000 0.0058
-10.750 -0.8632 0.02777 0.02440 -0.0569 1.0000 0.0059
-10.500 -0.8579 0.02589 0.02233 -0.0548 0.9989 0.0060
-10.250 -0.8329 0.02386 0.02009 -0.0564 0.9961 0.0061
-10.000 -0.8058 0.02222 0.01827 -0.0579 0.9936 0.0062
-9.750 -0.7798 0.02090 0.01680 -0.0587 0.9903 0.0064
-9.500 -0.7519 0.01958 0.01533 -0.0598 0.9875 0.0065
-9.250 -0.7222 0.01839 0.01399 -0.0611 0.9853 0.0067
-9.000 -0.6915 0.01723 0.01270 -0.0624 0.9837 0.0069
-8.750 -0.6623 0.01639 0.01176 -0.0633 0.9807 0.0072
-8.500 -0.6336 0.01568 0.01095 -0.0639 0.9767 0.0075
-8.250 -0.6043 0.01488 0.01004 -0.0645 0.9731 0.0078
-8.000 -0.5728 0.01437 0.00946 -0.0655 0.9701 0.0081
-7.750 -0.5542 0.01297 0.00789 -0.0642 0.9620 0.0087
-7.500 -0.5280 0.01239 0.00725 -0.0640 0.9568 0.0092
-7.250 -0.5044 0.01194 0.00674 -0.0632 0.9498 0.0096
-7.000 -0.4796 0.01155 0.00629 -0.0626 0.9437 0.0102
-6.750 -0.4550 0.01117 0.00584 -0.0619 0.9375 0.0108
-6.500 -0.4300 0.01087 0.00547 -0.0612 0.9309 0.0113
-6.250 -0.4063 0.01027 0.00479 -0.0604 0.9247 0.0126
-6.000 -0.3809 0.00999 0.00448 -0.0598 0.9180 0.0141
-5.750 -0.3550 0.00972 0.00415 -0.0593 0.9121 0.0161
-5.500 -0.3297 0.00936 0.00378 -0.0588 0.9051 0.0191
-5.250 -0.3039 0.00905 0.00342 -0.0583 0.8987 0.0226
-5.000 -0.2776 0.00881 0.00315 -0.0579 0.8918 0.0258
-4.750 -0.2515 0.00853 0.00286 -0.0574 0.8848 0.0314
-4.500 -0.2256 0.00821 0.00259 -0.0570 0.8776 0.0466
-4.250 -0.2013 0.00767 0.00227 -0.0564 0.8699 0.0998
-4.000 -0.1758 0.00731 0.00207 -0.0560 0.8620 0.1436
-3.750 -0.1494 0.00710 0.00192 -0.0556 0.8541 0.1737
-3.500 -0.1225 0.00694 0.00181 -0.0554 0.8454 0.1952
-3.250 -0.0956 0.00682 0.00170 -0.0551 0.8368 0.2132
-3.000 -0.0684 0.00670 0.00160 -0.0549 0.8270 0.2312
-2.750 -0.0412 0.00661 0.00152 -0.0546 0.8172 0.2485
-2.500 -0.0143 0.00651 0.00143 -0.0543 0.8067 0.2670
-2.250 0.0126 0.00641 0.00136 -0.0541 0.7951 0.2887
-2.000 0.0396 0.00634 0.00129 -0.0538 0.7826 0.3092
-1.750 0.0665 0.00625 0.00123 -0.0535 0.7692 0.3294
-1.500 0.0932 0.00619 0.00117 -0.0532 0.7541 0.3506
-1.250 0.1196 0.00613 0.00111 -0.0528 0.7375 0.3764
-1.000 0.1460 0.00606 0.00107 -0.0524 0.7216 0.4074
-0.750 0.1722 0.00596 0.00104 -0.0521 0.7070 0.4477
-0.500 0.1981 0.00583 0.00103 -0.0516 0.6925 0.4994
-0.250 0.2237 0.00570 0.00102 -0.0512 0.6783 0.5593
0.000 0.2492 0.00557 0.00103 -0.0506 0.6643 0.6178
0.250 0.2742 0.00544 0.00104 -0.0500 0.6505 0.6802
0.500 0.2984 0.00529 0.00106 -0.0491 0.6365 0.7477
0.750 0.3210 0.00511 0.00112 -0.0478 0.6228 0.8334
1.000 0.3450 0.00505 0.00122 -0.0466 0.6089 0.9057
1.250 0.3728 0.00512 0.00128 -0.0463 0.5944 0.9383
1.500 0.4032 0.00523 0.00134 -0.0467 0.5786 0.9569
1.750 0.4353 0.00535 0.00141 -0.0475 0.5633 0.9698
2.000 0.4728 0.00549 0.00147 -0.0496 0.5457 0.9765
2.250 0.5064 0.00564 0.00154 -0.0508 0.5264 0.9830
2.500 0.5459 0.00579 0.00162 -0.0533 0.5060 0.9861
2.750 0.5828 0.00596 0.00169 -0.0554 0.4825 0.9901
3.000 0.6167 0.00617 0.00179 -0.0567 0.4565 0.9939
3.250 0.6534 0.00637 0.00187 -0.0588 0.4281 0.9965
3.500 0.6895 0.00662 0.00198 -0.0608 0.3953 0.9992
3.750 0.7164 0.00686 0.00210 -0.0607 0.3659 1.0000
4.000 0.7376 0.00712 0.00224 -0.0595 0.3383 1.0000
4.250 0.7591 0.00737 0.00238 -0.0583 0.3131 1.0000
4.500 0.7806 0.00761 0.00254 -0.0571 0.2928 1.0000
4.750 0.8022 0.00786 0.00270 -0.0559 0.2727 1.0000
5.000 0.8240 0.00810 0.00287 -0.0547 0.2555 1.0000
5.250 0.8461 0.00832 0.00304 -0.0536 0.2414 1.0000
5.500 0.8683 0.00855 0.00322 -0.0525 0.2284 1.0000
5.750 0.8907 0.00877 0.00341 -0.0515 0.2164 1.0000
6.000 0.9130 0.00901 0.00361 -0.0504 0.2044 1.0000
6.250 0.9352 0.00928 0.00381 -0.0494 0.1901 1.0000
6.500 0.9574 0.00954 0.00402 -0.0484 0.1785 1.0000
6.750 0.9798 0.00980 0.00424 -0.0474 0.1675 1.0000
7.000 1.0025 0.01005 0.00447 -0.0464 0.1568 1.0000
7.250 1.0250 0.01032 0.00470 -0.0455 0.1462 1.0000
7.500 1.0474 0.01061 0.00496 -0.0445 0.1362 1.0000
7.750 1.0693 0.01093 0.00523 -0.0436 0.1249 1.0000
8.000 1.0914 0.01125 0.00551 -0.0426 0.1139 1.0000
8.250 1.1131 0.01160 0.00583 -0.0416 0.1028 1.0000
8.500 1.1341 0.01199 0.00617 -0.0405 0.0905 1.0000
8.750 1.1539 0.01247 0.00658 -0.0393 0.0764 1.0000
9.000 1.1727 0.01303 0.00704 -0.0379 0.0602 1.0000
9.250 1.1876 0.01384 0.00770 -0.0359 0.0381 1.0000
9.500 1.2017 0.01470 0.00845 -0.0338 0.0225 1.0000
9.750 1.2187 0.01532 0.00906 -0.0321 0.0177 1.0000
10.000 1.2347 0.01599 0.00974 -0.0303 0.0150 1.0000
10.250 1.2520 0.01652 0.01032 -0.0286 0.0142 1.0000
10.500 1.2677 0.01701 0.01087 -0.0267 0.0135 1.0000
10.750 1.2813 0.01755 0.01147 -0.0245 0.0129 1.0000
11.000 1.2941 0.01814 0.01211 -0.0222 0.0124 1.0000
11.250 1.3048 0.01887 0.01289 -0.0196 0.0118 1.0000
11.500 1.3119 0.01983 0.01394 -0.0167 0.0111 1.0000
11.750 1.3186 0.02083 0.01504 -0.0140 0.0108 1.0000
12.000 1.3316 0.02149 0.01576 -0.0122 0.0105 1.0000
12.250 1.3426 0.02230 0.01663 -0.0103 0.0101 1.0000
12.500 1.3535 0.02313 0.01753 -0.0086 0.0098 1.0000
12.750 1.3660 0.02390 0.01832 -0.0071 0.0092 1.0000
13.000 1.3697 0.02529 0.01983 -0.0048 0.0093 1.0000
13.250 1.3771 0.02648 0.02108 -0.0032 0.0088 1.0000
13.500 1.3818 0.02793 0.02260 -0.0015 0.0086 1.0000
13.750 1.3825 0.02977 0.02453 0.0002 0.0083 1.0000
14.000 1.3719 0.03267 0.02758 0.0021 0.0079 1.0000
14.250 1.3713 0.03495 0.02996 0.0031 0.0078 1.0000
14.500 1.3755 0.03688 0.03199 0.0038 0.0077 1.0000
14.750 1.3800 0.03887 0.03406 0.0042 0.0076 1.0000
15.000 1.3784 0.04162 0.03691 0.0044 0.0075 1.0000
15.250 1.3802 0.04410 0.03948 0.0044 0.0074 1.0000
15.500 1.3791 0.04702 0.04250 0.0042 0.0071 1.0000
15.750 1.3753 0.05043 0.04603 0.0036 0.0070 1.0000
16.000 1.3698 0.05421 0.04991 0.0027 0.0069 1.0000
16.250 1.3610 0.05861 0.05443 0.0015 0.0068 1.0000
16.500 1.3569 0.06255 0.05848 0.0001 0.0067 1.0000
16.750 1.3435 0.06797 0.06403 -0.0019 0.0067 1.0000
17.000 1.3343 0.07299 0.06916 -0.0039 0.0066 1.0000
17.250 1.3217 0.07874 0.07503 -0.0064 0.0065 1.0000
17.500 1.3044 0.08539 0.08181 -0.0094 0.0065 1.0000
17.750 1.2951 0.09096 0.08747 -0.0121 0.0064 1.0000
18.000 1.2807 0.09753 0.09416 -0.0153 0.0063 1.0000
18.250 1.2658 0.10424 0.10098 -0.0186 0.0063 1.0000
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Polar data table (+)
Polar graphs
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