SD6080 (9.2%) (sd6080-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD6080 (9.2%) (sd6080-il) Reynolds number: 500,000 Max Cl/Cd: 115.29 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd6080-il-500000.txt Download as CSV file: xf-sd6080-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: SD6080 (9.2%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3282 0.08563 0.08350 -0.0348 1.0000 0.0173
-8.000 -0.3302 0.08174 0.07967 -0.0375 1.0000 0.0180
-7.750 -0.3366 0.07839 0.07641 -0.0395 0.9979 0.0183
-7.500 -0.3121 0.07180 0.06981 -0.0508 0.9814 0.0184
-7.250 -0.2960 0.06499 0.06298 -0.0595 0.9691 0.0190
-7.000 -0.2734 0.06125 0.05920 -0.0652 0.9554 0.0195
-6.750 -0.2576 0.05767 0.05555 -0.0693 0.9371 0.0203
-6.500 -0.2463 0.05347 0.05123 -0.0730 0.9190 0.0210
-6.250 -0.2339 0.04874 0.04635 -0.0766 0.9037 0.0219
-6.000 -0.2124 0.04168 0.03880 -0.0814 0.8896 0.0242
-5.750 -0.2053 0.03528 0.03217 -0.0833 0.8782 0.0253
-5.500 -0.1860 0.03382 0.03063 -0.0834 0.8689 0.0262
-5.250 -0.1651 0.03154 0.02818 -0.0837 0.8591 0.0274
-5.000 -0.1422 0.02866 0.02498 -0.0840 0.8498 0.0296
-4.500 -0.0956 0.01706 0.01176 -0.0828 0.8331 0.0175
-4.250 -0.0702 0.01461 0.00887 -0.0822 0.8256 0.0163
-4.000 -0.0434 0.01318 0.00718 -0.0817 0.8169 0.0161
-3.750 -0.0166 0.01225 0.00608 -0.0813 0.8092 0.0166
-3.500 0.0104 0.01153 0.00523 -0.0809 0.8008 0.0173
-3.250 0.0375 0.01097 0.00456 -0.0806 0.7929 0.0179
-3.000 0.0643 0.01032 0.00382 -0.0804 0.7849 0.0197
-2.750 0.0918 0.00992 0.00337 -0.0802 0.7769 0.0214
-2.500 0.1193 0.00959 0.00293 -0.0800 0.7693 0.0236
-2.250 0.1472 0.00919 0.00250 -0.0798 0.7613 0.0315
-2.000 0.1744 0.00869 0.00219 -0.0797 0.7540 0.0938
-1.750 0.2018 0.00837 0.00207 -0.0797 0.7460 0.1555
-1.500 0.2289 0.00804 0.00196 -0.0797 0.7389 0.2436
-1.250 0.2555 0.00754 0.00192 -0.0798 0.7309 0.3906
-1.000 0.2815 0.00713 0.00189 -0.0796 0.7241 0.5339
-0.750 0.3064 0.00666 0.00189 -0.0789 0.7161 0.6885
-0.500 0.3264 0.00622 0.00191 -0.0767 0.7094 0.8593
-0.250 0.3718 0.00601 0.00180 -0.0801 0.7014 1.0000
0.000 0.3990 0.00609 0.00175 -0.0798 0.6943 1.0000
0.250 0.4265 0.00614 0.00174 -0.0797 0.6860 1.0000
0.500 0.4538 0.00622 0.00172 -0.0795 0.6785 1.0000
0.750 0.4813 0.00628 0.00171 -0.0794 0.6699 1.0000
1.000 0.5088 0.00636 0.00171 -0.0793 0.6619 1.0000
1.250 0.5363 0.00643 0.00172 -0.0791 0.6535 1.0000
1.500 0.5639 0.00650 0.00175 -0.0790 0.6450 1.0000
1.750 0.5912 0.00661 0.00177 -0.0789 0.6367 1.0000
2.000 0.6188 0.00667 0.00182 -0.0788 0.6273 1.0000
2.250 0.6463 0.00676 0.00186 -0.0787 0.6183 1.0000
2.500 0.6736 0.00686 0.00192 -0.0786 0.6087 1.0000
2.750 0.7011 0.00694 0.00199 -0.0785 0.5985 1.0000
3.000 0.7284 0.00705 0.00206 -0.0783 0.5887 1.0000
3.500 0.7828 0.00727 0.00223 -0.0781 0.5667 1.0000
3.750 0.8100 0.00738 0.00233 -0.0780 0.5548 1.0000
4.000 0.8370 0.00751 0.00244 -0.0778 0.5422 1.0000
4.250 0.8638 0.00765 0.00255 -0.0776 0.5285 1.0000
4.500 0.8905 0.00781 0.00270 -0.0774 0.5137 1.0000
4.750 0.9170 0.00798 0.00284 -0.0772 0.4972 1.0000
5.000 0.9431 0.00818 0.00301 -0.0770 0.4795 1.0000
5.250 0.9691 0.00841 0.00319 -0.0767 0.4599 1.0000
5.500 0.9947 0.00866 0.00340 -0.0764 0.4373 1.0000
5.750 1.0196 0.00898 0.00364 -0.0760 0.4103 1.0000
6.000 1.0432 0.00942 0.00393 -0.0754 0.3737 1.0000
6.250 1.0659 0.00996 0.00429 -0.0748 0.3314 1.0000
6.500 1.0884 0.01053 0.00468 -0.0741 0.2922 1.0000
6.750 1.1109 0.01109 0.00509 -0.0735 0.2585 1.0000
7.000 1.1327 0.01170 0.00555 -0.0728 0.2237 1.0000
7.250 1.1540 0.01235 0.00605 -0.0720 0.1913 1.0000
7.500 1.1755 0.01297 0.00654 -0.0713 0.1635 1.0000
7.750 1.1962 0.01364 0.00707 -0.0704 0.1359 1.0000
8.000 1.2163 0.01434 0.00764 -0.0695 0.1096 1.0000
8.250 1.2355 0.01510 0.00828 -0.0685 0.0844 1.0000
8.500 1.2521 0.01605 0.00905 -0.0671 0.0543 1.0000
8.750 1.2633 0.01746 0.01020 -0.0649 0.0236 1.0000
9.250 1.2961 0.01914 0.01197 -0.0618 0.0163 1.0000
9.500 1.3118 0.01994 0.01284 -0.0602 0.0152 1.0000
9.750 1.3233 0.02088 0.01386 -0.0580 0.0142 1.0000
10.000 1.3290 0.02203 0.01511 -0.0550 0.0136 1.0000
10.250 1.3323 0.02337 0.01655 -0.0519 0.0131 1.0000
10.500 1.3400 0.02450 0.01779 -0.0496 0.0129 1.0000
10.750 1.3463 0.02580 0.01920 -0.0474 0.0127 1.0000
11.000 1.3516 0.02727 0.02076 -0.0454 0.0124 1.0000
11.250 1.3561 0.02888 0.02249 -0.0435 0.0122 1.0000
11.500 1.3602 0.03063 0.02435 -0.0418 0.0119 1.0000
11.750 1.3639 0.03251 0.02634 -0.0402 0.0117 1.0000
12.000 1.3678 0.03445 0.02839 -0.0389 0.0113 1.0000
12.250 1.3719 0.03644 0.03046 -0.0378 0.0110 1.0000
12.500 1.3749 0.03862 0.03272 -0.0369 0.0107 1.0000
12.750 1.3768 0.04101 0.03522 -0.0359 0.0105 1.0000
13.000 1.3778 0.04358 0.03789 -0.0351 0.0104 1.0000
13.250 1.3783 0.04632 0.04073 -0.0344 0.0102 1.0000
13.500 1.3782 0.04925 0.04378 -0.0337 0.0100 1.0000
13.750 1.3785 0.05224 0.04690 -0.0332 0.0100 1.0000
14.000 1.3768 0.05570 0.05051 -0.0325 0.0098 1.0000
14.250 1.3761 0.05903 0.05399 -0.0323 0.0098 1.0000
14.500 1.3721 0.06305 0.05820 -0.0322 0.0097 1.0000
14.750 1.3647 0.06763 0.06299 -0.0324 0.0096 1.0000
15.000 1.3567 0.07231 0.06787 -0.0332 0.0096 1.0000
15.500 1.3374 0.08243 0.07836 -0.0362 0.0096 1.0000
15.750 1.3260 0.08797 0.08409 -0.0387 0.0096 1.0000
16.000 1.3125 0.09429 0.09060 -0.0412 0.0096 1.0000
16.250 1.2976 0.10108 0.09758 -0.0444 0.0096 1.0000
16.500 1.2844 0.10784 0.10451 -0.0480 0.0096 1.0000
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Polar data table (+)
Polar graphs
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