SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.54 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7080-il-1000000.txt Download as CSV file: xf-sd7080-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: SD7080 (9.2%)
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 -0.4359 0.08221 0.08061 -0.0319 1.0000 0.0128
-8.750 -0.4386 0.07828 0.07670 -0.0336 1.0000 0.0131
-8.500 -0.4438 0.07436 0.07281 -0.0352 1.0000 0.0134
-8.250 -0.4587 0.07061 0.06912 -0.0356 1.0000 0.0137
-8.000 -0.4776 0.06707 0.06563 -0.0366 0.9990 0.0136
-7.750 -0.4587 0.05267 0.05107 -0.0573 0.9935 0.0142
-7.500 -0.4403 0.04027 0.03818 -0.0674 0.9881 0.0151
-7.250 -0.4178 0.03452 0.03198 -0.0725 0.9854 0.0152
-7.000 -0.4075 0.02555 0.02242 -0.0762 0.9803 0.0162
-6.750 -0.3811 0.02386 0.02061 -0.0771 0.9766 0.0166
-6.500 -0.3540 0.02253 0.01915 -0.0780 0.9732 0.0173
-6.250 -0.3381 0.01605 0.01179 -0.0761 0.9663 0.0134
-6.000 -0.3145 0.01452 0.01002 -0.0753 0.9612 0.0134
-5.750 -0.2901 0.01350 0.00884 -0.0746 0.9567 0.0136
-5.500 -0.2665 0.01260 0.00782 -0.0737 0.9508 0.0137
-5.250 -0.2424 0.01182 0.00693 -0.0728 0.9457 0.0139
-5.000 -0.2177 0.01112 0.00615 -0.0721 0.9405 0.0140
-4.750 -0.1929 0.01050 0.00546 -0.0713 0.9347 0.0142
-4.500 -0.1676 0.01005 0.00494 -0.0706 0.9295 0.0146
-4.250 -0.1417 0.00959 0.00442 -0.0701 0.9236 0.0149
-4.000 -0.1159 0.00916 0.00393 -0.0695 0.9175 0.0151
-3.750 -0.0902 0.00860 0.00329 -0.0690 0.9115 0.0156
-3.500 -0.0640 0.00811 0.00272 -0.0685 0.9043 0.0166
-3.250 -0.0373 0.00783 0.00239 -0.0681 0.8976 0.0175
-3.000 -0.0101 0.00760 0.00212 -0.0678 0.8894 0.0185
-2.750 0.0171 0.00741 0.00189 -0.0675 0.8814 0.0197
-2.500 0.0444 0.00722 0.00165 -0.0672 0.8722 0.0227
-2.250 0.0712 0.00680 0.00143 -0.0669 0.8620 0.0728
-2.000 0.0978 0.00645 0.00128 -0.0667 0.8511 0.1407
-1.750 0.1245 0.00614 0.00116 -0.0665 0.8386 0.2107
-1.500 0.1513 0.00586 0.00107 -0.0663 0.8244 0.2847
-1.250 0.1779 0.00559 0.00099 -0.0661 0.8081 0.3684
-1.000 0.2038 0.00524 0.00095 -0.0659 0.7894 0.4866
-0.750 0.2298 0.00503 0.00092 -0.0655 0.7690 0.5807
-0.500 0.2556 0.00484 0.00092 -0.0650 0.7465 0.6709
-0.250 0.2811 0.00475 0.00094 -0.0643 0.7233 0.7419
0.000 0.3067 0.00472 0.00097 -0.0637 0.6993 0.7923
0.250 0.3321 0.00473 0.00099 -0.0630 0.6758 0.8332
0.750 0.3802 0.00477 0.00107 -0.0608 0.6288 0.9172
1.000 0.4064 0.00484 0.00110 -0.0602 0.6052 0.9570
1.250 0.4436 0.00496 0.00111 -0.0622 0.5791 0.9846
1.500 0.4809 0.00510 0.00114 -0.0643 0.5524 1.0000
1.750 0.5065 0.00526 0.00119 -0.0638 0.5291 1.0000
2.000 0.5323 0.00544 0.00125 -0.0634 0.5051 1.0000
2.250 0.5586 0.00560 0.00131 -0.0631 0.4822 1.0000
2.500 0.5848 0.00578 0.00140 -0.0628 0.4591 1.0000
2.750 0.6111 0.00596 0.00148 -0.0625 0.4363 1.0000
3.000 0.6375 0.00615 0.00157 -0.0622 0.4147 1.0000
3.250 0.6639 0.00635 0.00167 -0.0620 0.3925 1.0000
3.500 0.6903 0.00655 0.00179 -0.0617 0.3717 1.0000
3.750 0.7168 0.00675 0.00191 -0.0615 0.3509 1.0000
4.250 0.7694 0.00719 0.00218 -0.0610 0.3111 1.0000
4.500 0.7958 0.00740 0.00234 -0.0607 0.2937 1.0000
4.750 0.8219 0.00765 0.00251 -0.0605 0.2741 1.0000
5.000 0.8480 0.00789 0.00268 -0.0602 0.2570 1.0000
5.250 0.8740 0.00814 0.00287 -0.0599 0.2372 1.0000
5.500 0.8994 0.00846 0.00308 -0.0596 0.2149 1.0000
5.750 0.9252 0.00873 0.00329 -0.0593 0.1983 1.0000
6.000 0.9506 0.00904 0.00352 -0.0590 0.1795 1.0000
6.250 0.9755 0.00940 0.00379 -0.0586 0.1592 1.0000
6.500 1.0007 0.00972 0.00405 -0.0582 0.1426 1.0000
6.750 1.0255 0.01009 0.00433 -0.0578 0.1247 1.0000
7.000 1.0501 0.01047 0.00464 -0.0573 0.1092 1.0000
7.250 1.0745 0.01086 0.00496 -0.0569 0.0952 1.0000
7.500 1.0984 0.01129 0.00532 -0.0564 0.0796 1.0000
7.750 1.1222 0.01174 0.00570 -0.0558 0.0653 1.0000
8.000 1.1456 0.01221 0.00610 -0.0552 0.0525 1.0000
8.250 1.1685 0.01272 0.00656 -0.0546 0.0406 1.0000
8.500 1.1902 0.01335 0.00709 -0.0538 0.0281 1.0000
8.750 1.2092 0.01427 0.00788 -0.0526 0.0120 1.0000
9.000 1.2310 0.01487 0.00849 -0.0517 0.0095 1.0000
9.250 1.2520 0.01552 0.00920 -0.0507 0.0081 1.0000
9.500 1.2737 0.01607 0.00983 -0.0498 0.0076 1.0000
9.750 1.2945 0.01668 0.01050 -0.0488 0.0071 1.0000
10.000 1.3146 0.01733 0.01122 -0.0478 0.0067 1.0000
10.250 1.3332 0.01808 0.01202 -0.0465 0.0063 1.0000
10.500 1.3448 0.01943 0.01352 -0.0442 0.0058 1.0000
10.750 1.3623 0.02012 0.01429 -0.0429 0.0057 1.0000
11.000 1.3779 0.02092 0.01517 -0.0412 0.0056 1.0000
11.250 1.3911 0.02180 0.01615 -0.0392 0.0055 1.0000
11.500 1.4004 0.02268 0.01712 -0.0366 0.0054 1.0000
11.750 1.4080 0.02362 0.01815 -0.0338 0.0053 1.0000
12.000 1.4126 0.02479 0.01942 -0.0309 0.0052 1.0000
12.250 1.4187 0.02591 0.02064 -0.0284 0.0051 1.0000
12.500 1.4213 0.02733 0.02217 -0.0258 0.0050 1.0000
12.750 1.4246 0.02879 0.02373 -0.0235 0.0049 1.0000
13.000 1.4249 0.03057 0.02562 -0.0213 0.0049 1.0000
13.250 1.4264 0.03238 0.02754 -0.0196 0.0048 1.0000
13.500 1.4250 0.03457 0.02985 -0.0180 0.0048 1.0000
13.750 1.4232 0.03699 0.03238 -0.0169 0.0047 1.0000
14.000 1.4216 0.03957 0.03509 -0.0163 0.0046 1.0000
14.250 1.4122 0.04326 0.03893 -0.0160 0.0047 1.0000
14.500 1.4102 0.04636 0.04213 -0.0163 0.0046 1.0000
14.750 1.4026 0.05043 0.04633 -0.0172 0.0046 1.0000
15.000 1.3958 0.05465 0.05067 -0.0185 0.0045 1.0000
15.250 1.3876 0.05935 0.05550 -0.0203 0.0045 1.0000
15.500 1.3757 0.06488 0.06116 -0.0226 0.0045 1.0000
15.750 1.3640 0.07063 0.06705 -0.0253 0.0044 1.0000
16.000 1.3505 0.07694 0.07350 -0.0284 0.0044 1.0000
16.250 1.3349 0.08382 0.08053 -0.0319 0.0045 1.0000
16.500 1.3235 0.09027 0.08707 -0.0354 0.0044 1.0000
16.750 1.3080 0.09761 0.09456 -0.0392 0.0044 1.0000
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Polar data table (+)
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