SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD2083 (9.0%) (sd2083-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.3 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd2083-il-1000000.txt Download as CSV file: xf-sd2083-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD2083 (9.0%)
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3991 0.08557 0.08401 -0.0359 1.0000 0.0110
-8.750 -0.3996 0.08193 0.08039 -0.0375 1.0000 0.0110
-8.500 -0.4023 0.07837 0.07687 -0.0389 1.0000 0.0116
-8.250 -0.3940 0.07309 0.07161 -0.0450 0.9870 0.0119
-8.000 -0.3742 0.06488 0.06338 -0.0592 0.9729 0.0127
-6.750 -0.3720 0.02844 0.02547 -0.0733 0.9039 0.0141
-6.500 -0.3541 0.02676 0.02366 -0.0730 0.8983 0.0146
-6.250 -0.3336 0.02540 0.02217 -0.0726 0.8926 0.0151
-6.000 -0.3133 0.02374 0.02031 -0.0720 0.8875 0.0157
-5.750 -0.2920 0.02181 0.01814 -0.0714 0.8822 0.0166
-5.500 -0.2693 0.02008 0.01616 -0.0707 0.8770 0.0176
-5.250 -0.2508 0.01497 0.01020 -0.0683 0.8720 0.0140
-5.000 -0.2246 0.01415 0.00924 -0.0679 0.8671 0.0137
-4.750 -0.1999 0.01264 0.00753 -0.0673 0.8623 0.0138
-4.500 -0.1753 0.01134 0.00606 -0.0667 0.8579 0.0141
-4.250 -0.1498 0.01044 0.00509 -0.0662 0.8530 0.0144
-4.000 -0.1238 0.00982 0.00439 -0.0658 0.8481 0.0146
-3.750 -0.0978 0.00932 0.00380 -0.0654 0.8436 0.0149
-3.500 -0.0711 0.00888 0.00332 -0.0652 0.8385 0.0153
-3.250 -0.0443 0.00855 0.00293 -0.0649 0.8335 0.0160
-3.000 -0.0174 0.00824 0.00254 -0.0647 0.8288 0.0165
-2.750 0.0099 0.00795 0.00221 -0.0645 0.8233 0.0172
-2.500 0.0372 0.00773 0.00192 -0.0643 0.8180 0.0184
-2.250 0.0648 0.00757 0.00172 -0.0641 0.8125 0.0192
-2.000 0.0924 0.00737 0.00148 -0.0640 0.8063 0.0227
-1.750 0.1192 0.00709 0.00131 -0.0637 0.8004 0.0597
-1.500 0.1456 0.00669 0.00120 -0.0636 0.7936 0.1418
-1.250 0.1714 0.00629 0.00110 -0.0634 0.7872 0.2511
-1.000 0.1976 0.00591 0.00104 -0.0632 0.7799 0.3568
-0.750 0.2232 0.00557 0.00099 -0.0629 0.7728 0.4717
-0.500 0.2486 0.00520 0.00097 -0.0625 0.7646 0.5910
-0.250 0.2704 0.00469 0.00099 -0.0612 0.7570 0.7643
0.000 0.2917 0.00432 0.00104 -0.0594 0.7483 0.9052
0.250 0.3324 0.00430 0.00106 -0.0619 0.7391 0.9681
0.500 0.3810 0.00436 0.00104 -0.0665 0.7299 0.9873
0.750 0.4219 0.00440 0.00104 -0.0693 0.7200 0.9949
1.000 0.4643 0.00443 0.00102 -0.0726 0.7100 0.9999
1.250 0.4900 0.00448 0.00101 -0.0722 0.6989 1.0000
1.500 0.5151 0.00454 0.00102 -0.0716 0.6872 1.0000
1.750 0.5402 0.00461 0.00104 -0.0710 0.6739 1.0000
2.000 0.5654 0.00469 0.00107 -0.0704 0.6592 1.0000
2.250 0.5905 0.00479 0.00111 -0.0699 0.6423 1.0000
2.500 0.6154 0.00490 0.00117 -0.0693 0.6231 1.0000
2.750 0.6400 0.00505 0.00123 -0.0686 0.6019 1.0000
3.000 0.6645 0.00522 0.00131 -0.0680 0.5771 1.0000
3.250 0.6886 0.00542 0.00140 -0.0672 0.5484 1.0000
3.500 0.7124 0.00566 0.00153 -0.0665 0.5152 1.0000
3.750 0.7355 0.00597 0.00168 -0.0657 0.4764 1.0000
4.000 0.7586 0.00629 0.00184 -0.0648 0.4365 1.0000
4.250 0.7814 0.00663 0.00203 -0.0640 0.3972 1.0000
4.500 0.8042 0.00700 0.00223 -0.0631 0.3584 1.0000
4.750 0.8262 0.00744 0.00248 -0.0622 0.3124 1.0000
5.000 0.8484 0.00788 0.00273 -0.0613 0.2701 1.0000
5.250 0.8707 0.00832 0.00298 -0.0604 0.2323 1.0000
5.500 0.8938 0.00869 0.00323 -0.0597 0.2047 1.0000
5.750 0.9168 0.00907 0.00350 -0.0590 0.1778 1.0000
6.000 0.9392 0.00951 0.00380 -0.0582 0.1472 1.0000
6.250 0.9603 0.01006 0.00415 -0.0572 0.1122 1.0000
6.500 0.9818 0.01057 0.00452 -0.0563 0.0841 1.0000
6.750 1.0028 0.01114 0.00494 -0.0553 0.0574 1.0000
7.000 1.0207 0.01199 0.00556 -0.0538 0.0225 1.0000
7.250 1.0406 0.01267 0.00616 -0.0525 0.0097 1.0000
7.500 1.0623 0.01316 0.00668 -0.0515 0.0082 1.0000
7.750 1.0825 0.01380 0.00741 -0.0503 0.0072 1.0000
8.000 1.1040 0.01427 0.00793 -0.0493 0.0069 1.0000
8.250 1.1250 0.01477 0.00849 -0.0483 0.0065 1.0000
8.500 1.1450 0.01536 0.00914 -0.0471 0.0062 1.0000
8.750 1.1641 0.01598 0.00983 -0.0458 0.0060 1.0000
9.000 1.1822 0.01666 0.01057 -0.0443 0.0058 1.0000
9.250 1.1990 0.01740 0.01139 -0.0427 0.0056 1.0000
9.500 1.2145 0.01819 0.01225 -0.0409 0.0054 1.0000
9.750 1.2273 0.01910 0.01324 -0.0387 0.0052 1.0000
10.000 1.2362 0.02004 0.01427 -0.0358 0.0052 1.0000
10.250 1.2427 0.02113 0.01546 -0.0327 0.0051 1.0000
10.500 1.2378 0.02323 0.01771 -0.0283 0.0048 1.0000
10.750 1.2424 0.02480 0.01940 -0.0255 0.0048 1.0000
11.000 1.2538 0.02572 0.02041 -0.0236 0.0047 1.0000
11.250 1.2609 0.02711 0.02190 -0.0214 0.0046 1.0000
11.500 1.2693 0.02837 0.02328 -0.0195 0.0046 1.0000
11.750 1.2772 0.02968 0.02471 -0.0176 0.0043 1.0000
12.000 1.2810 0.03148 0.02664 -0.0156 0.0043 1.0000
12.250 1.2825 0.03359 0.02892 -0.0135 0.0043 1.0000
12.500 1.2842 0.03565 0.03112 -0.0118 0.0042 1.0000
12.750 1.2814 0.03836 0.03401 -0.0099 0.0043 1.0000
13.000 1.2777 0.04115 0.03697 -0.0085 0.0043 1.0000
13.250 1.2705 0.04448 0.04049 -0.0072 0.0043 1.0000
13.500 1.2612 0.04814 0.04435 -0.0064 0.0043 1.0000
13.750 1.2517 0.05196 0.04834 -0.0061 0.0044 1.0000
14.000 1.2384 0.05653 0.05309 -0.0064 0.0044 1.0000
14.250 1.2230 0.06164 0.05839 -0.0074 0.0044 1.0000
14.500 1.2072 0.06724 0.06415 -0.0091 0.0045 1.0000
14.750 1.1876 0.07393 0.07103 -0.0118 0.0045 1.0000
15.000 1.1693 0.08098 0.07825 -0.0153 0.0046 1.0000
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Polar data table (+)
Polar graphs
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