SD7080 (9.2%) (sd7080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7080 (9.2%) (sd7080-il) Reynolds number: 200,000 Max Cl/Cd: 69.43 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7080-il-200000.txt Download as CSV file: xf-sd7080-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4095 0.08735 0.08386 -0.0306 1.0000 0.0520
-8.250 -0.4112 0.08407 0.08064 -0.0317 1.0000 0.0537
-8.000 -0.4166 0.08087 0.07750 -0.0329 1.0000 0.0550
-7.750 -0.4310 0.07780 0.07453 -0.0337 1.0000 0.0561
-7.250 -0.4696 0.06881 0.06541 -0.0434 1.0000 0.0583
-7.000 -0.4777 0.06590 0.06230 -0.0432 1.0000 0.0586
-6.750 -0.4793 0.05973 0.05629 -0.0420 1.0000 0.0598
-6.500 -0.4736 0.05747 0.05409 -0.0398 1.0000 0.0608
-6.250 -0.4682 0.05529 0.05193 -0.0382 1.0000 0.0622
-6.000 -0.4624 0.05265 0.04923 -0.0374 1.0000 0.0642
-5.750 -0.4548 0.04921 0.04559 -0.0377 1.0000 0.0684
-5.500 -0.4480 0.04425 0.04018 -0.0389 1.0000 0.0736
-5.250 -0.4353 0.04201 0.03798 -0.0378 1.0000 0.0755
-5.000 -0.4210 0.03981 0.03566 -0.0371 1.0000 0.0793
-4.750 -0.3924 0.03643 0.03197 -0.0398 0.9973 0.0894
-4.500 -0.3500 0.02516 0.01901 -0.0411 0.9954 0.0430
-4.250 -0.3131 0.02139 0.01448 -0.0424 0.9926 0.0384
-4.000 -0.2754 0.01957 0.01228 -0.0440 0.9885 0.0374
-3.750 -0.2361 0.01814 0.01068 -0.0462 0.9849 0.0378
-3.500 -0.1995 0.01702 0.00948 -0.0479 0.9801 0.0393
-3.250 -0.1606 0.01632 0.00875 -0.0501 0.9748 0.0433
-3.000 -0.1176 0.01561 0.00797 -0.0530 0.9711 0.0464
-2.750 -0.0850 0.01460 0.00698 -0.0540 0.9636 0.0533
-2.500 -0.0442 0.01334 0.00612 -0.0568 0.9592 0.1311
-2.250 -0.0110 0.01226 0.00592 -0.0585 0.9524 0.3374
-2.000 0.0241 0.01139 0.00587 -0.0602 0.9465 0.5505
-1.750 0.0554 0.01077 0.00595 -0.0600 0.9406 0.7400
-1.500 0.0854 0.01047 0.00591 -0.0592 0.9331 0.8467
-1.250 0.1356 0.01026 0.00573 -0.0624 0.9305 0.9359
-1.000 0.2036 0.01003 0.00539 -0.0700 0.9295 0.9822
-0.750 0.2538 0.00983 0.00507 -0.0745 0.9222 1.0000
-0.500 0.2907 0.00959 0.00472 -0.0760 0.9143 1.0000
-0.250 0.3157 0.00943 0.00448 -0.0751 0.9013 1.0000
0.000 0.3403 0.00929 0.00425 -0.0740 0.8880 1.0000
0.250 0.3648 0.00915 0.00403 -0.0729 0.8742 1.0000
0.500 0.3895 0.00902 0.00383 -0.0718 0.8595 1.0000
0.750 0.4143 0.00891 0.00364 -0.0706 0.8438 1.0000
1.000 0.4396 0.00881 0.00346 -0.0696 0.8271 1.0000
1.250 0.4640 0.00878 0.00335 -0.0685 0.8066 1.0000
1.500 0.4895 0.00876 0.00323 -0.0675 0.7858 1.0000
1.750 0.5147 0.00879 0.00317 -0.0666 0.7627 1.0000
2.000 0.5401 0.00887 0.00311 -0.0657 0.7389 1.0000
2.250 0.5652 0.00899 0.00311 -0.0648 0.7130 1.0000
2.500 0.5902 0.00916 0.00317 -0.0639 0.6863 1.0000
2.750 0.6150 0.00935 0.00323 -0.0631 0.6591 1.0000
3.000 0.6398 0.00958 0.00333 -0.0623 0.6319 1.0000
3.250 0.6644 0.00982 0.00345 -0.0615 0.6044 1.0000
3.500 0.6889 0.01009 0.00361 -0.0607 0.5769 1.0000
3.750 0.7133 0.01038 0.00377 -0.0599 0.5497 1.0000
4.000 0.7376 0.01068 0.00397 -0.0592 0.5221 1.0000
4.250 0.7619 0.01099 0.00418 -0.0585 0.4951 1.0000
4.500 0.7860 0.01132 0.00444 -0.0577 0.4684 1.0000
4.750 0.8100 0.01167 0.00470 -0.0570 0.4427 1.0000
5.000 0.8338 0.01205 0.00497 -0.0563 0.4177 1.0000
5.250 0.8577 0.01241 0.00528 -0.0556 0.3924 1.0000
5.500 0.8814 0.01281 0.00563 -0.0549 0.3681 1.0000
5.750 0.9046 0.01325 0.00598 -0.0541 0.3450 1.0000
6.000 0.9282 0.01366 0.00637 -0.0534 0.3213 1.0000
6.250 0.9512 0.01413 0.00677 -0.0527 0.2991 1.0000
6.500 0.9741 0.01459 0.00722 -0.0519 0.2764 1.0000
6.750 0.9966 0.01509 0.00768 -0.0512 0.2544 1.0000
7.000 1.0189 0.01561 0.00816 -0.0503 0.2328 1.0000
7.250 1.0407 0.01618 0.00869 -0.0495 0.2127 1.0000
7.500 1.0625 0.01675 0.00927 -0.0487 0.1930 1.0000
7.750 1.0833 0.01742 0.00989 -0.0477 0.1748 1.0000
8.000 1.1040 0.01810 0.01056 -0.0467 0.1570 1.0000
8.250 1.1245 0.01873 0.01120 -0.0458 0.1379 1.0000
8.500 1.1434 0.01948 0.01189 -0.0447 0.1193 1.0000
8.750 1.1635 0.02014 0.01258 -0.0438 0.1010 1.0000
9.000 1.1820 0.02095 0.01338 -0.0426 0.0855 1.0000
9.250 1.1989 0.02188 0.01428 -0.0413 0.0704 1.0000
9.500 1.2132 0.02307 0.01545 -0.0396 0.0536 1.0000
9.750 1.2216 0.02477 0.01711 -0.0371 0.0383 1.0000
10.000 1.2275 0.02654 0.01895 -0.0342 0.0321 1.0000
10.250 1.2322 0.02809 0.02055 -0.0312 0.0289 1.0000
10.500 1.2353 0.02990 0.02247 -0.0283 0.0263 1.0000
10.750 1.2431 0.03134 0.02404 -0.0260 0.0245 1.0000
11.000 1.2492 0.03293 0.02573 -0.0238 0.0231 1.0000
11.250 1.2534 0.03480 0.02767 -0.0218 0.0220 1.0000
11.500 1.2565 0.03728 0.03022 -0.0198 0.0212 1.0000
11.750 1.2615 0.04017 0.03326 -0.0181 0.0206 1.0000
12.000 1.2662 0.04240 0.03571 -0.0164 0.0201 1.0000
12.250 1.2694 0.04497 0.03850 -0.0150 0.0199 1.0000
12.500 1.2695 0.04779 0.04157 -0.0137 0.0195 1.0000
12.750 1.2671 0.05098 0.04503 -0.0127 0.0194 1.0000
13.000 1.2620 0.05448 0.04877 -0.0120 0.0193 1.0000
13.250 1.2533 0.05851 0.05305 -0.0119 0.0192 1.0000
13.500 1.2422 0.06293 0.05773 -0.0124 0.0192 1.0000
13.750 1.2287 0.06793 0.06297 -0.0137 0.0192 1.0000
14.000 1.2128 0.07356 0.06884 -0.0158 0.0192 1.0000
14.250 1.1957 0.07975 0.07526 -0.0187 0.0193 1.0000
14.500 1.1769 0.08665 0.08237 -0.0224 0.0194 1.0000
14.750 1.1569 0.09426 0.09018 -0.0270 0.0196 1.0000
15.000 1.1360 0.10263 0.09874 -0.0323 0.0197 1.0000
15.250 1.1145 0.11173 0.10798 -0.0382 0.0200 1.0000
15.500 1.0911 0.12190 0.11830 -0.0449 0.0202 1.0000
15.750 1.0671 0.13291 0.12944 -0.0520 0.0204 1.0000
16.000 1.0443 0.14433 0.14098 -0.0592 0.0208 1.0000
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Polar data table (+)
Polar graphs
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