SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 100,000 Max Cl/Cd: 47.58 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7090-il-100000-n5.txt Download as CSV file: xf-sd7090-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7090 (10%)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5130 0.08692 0.08169 -0.0297 1.0000 0.0331
-9.500 -0.5227 0.08095 0.07579 -0.0329 1.0000 0.0330
-9.250 -0.5389 0.07340 0.06832 -0.0377 1.0000 0.0329
-9.000 -0.5663 0.06441 0.05936 -0.0445 1.0000 0.0320
-8.750 -0.5933 0.05826 0.05309 -0.0459 1.0000 0.0315
-8.500 -0.6118 0.05284 0.04744 -0.0459 1.0000 0.0315
-8.250 -0.6222 0.04810 0.04240 -0.0450 1.0000 0.0318
-8.000 -0.6265 0.04373 0.03765 -0.0436 1.0000 0.0322
-7.750 -0.6252 0.03979 0.03326 -0.0420 1.0000 0.0325
-7.500 -0.6191 0.03629 0.02929 -0.0402 1.0000 0.0330
-7.250 -0.6086 0.03332 0.02585 -0.0384 1.0000 0.0336
-7.000 -0.5950 0.03075 0.02282 -0.0367 1.0000 0.0344
-6.750 -0.5790 0.02875 0.02048 -0.0351 1.0000 0.0358
-6.500 -0.5612 0.02757 0.01926 -0.0339 1.0000 0.0375
-6.250 -0.5427 0.02634 0.01784 -0.0326 1.0000 0.0394
-6.000 -0.5235 0.02489 0.01617 -0.0311 1.0000 0.0410
-5.750 -0.5037 0.02355 0.01460 -0.0297 1.0000 0.0428
-5.500 -0.4836 0.02236 0.01322 -0.0283 1.0000 0.0447
-5.250 -0.4644 0.02140 0.01230 -0.0271 1.0000 0.0475
-5.000 -0.4444 0.02069 0.01151 -0.0258 1.0000 0.0520
-4.750 -0.4246 0.01984 0.01058 -0.0244 1.0000 0.0566
-4.500 -0.4051 0.01912 0.00987 -0.0232 1.0000 0.0620
-4.250 -0.3853 0.01848 0.00919 -0.0219 1.0000 0.0699
-4.000 -0.3523 0.01789 0.00860 -0.0233 0.9952 0.0836
-3.750 -0.3158 0.01735 0.00811 -0.0255 0.9882 0.1030
-3.500 -0.2791 0.01680 0.00766 -0.0276 0.9811 0.1280
-3.250 -0.2435 0.01624 0.00721 -0.0295 0.9730 0.1591
-3.000 -0.2096 0.01567 0.00683 -0.0310 0.9639 0.2057
-2.750 -0.1738 0.01511 0.00654 -0.0329 0.9559 0.2727
-2.500 -0.1412 0.01453 0.00628 -0.0341 0.9458 0.3569
-2.250 -0.1094 0.01395 0.00610 -0.0349 0.9356 0.4587
-2.000 -0.0753 0.01340 0.00601 -0.0358 0.9272 0.5772
-1.750 -0.0443 0.01302 0.00596 -0.0356 0.9168 0.6834
-1.500 -0.0133 0.01277 0.00591 -0.0352 0.9055 0.7678
-1.250 0.0231 0.01260 0.00584 -0.0358 0.8952 0.8372
-1.000 0.0693 0.01250 0.00573 -0.0385 0.8856 0.8927
-0.750 0.1204 0.01244 0.00559 -0.0425 0.8735 0.9317
-0.500 0.1730 0.01236 0.00540 -0.0470 0.8603 0.9599
-0.250 0.2259 0.01227 0.00517 -0.0517 0.8449 0.9806
0.000 0.2787 0.01214 0.00492 -0.0566 0.8273 0.9969
0.250 0.3112 0.01209 0.00473 -0.0574 0.8062 1.0000
0.500 0.3369 0.01209 0.00461 -0.0569 0.7841 1.0000
0.750 0.3625 0.01212 0.00451 -0.0562 0.7623 1.0000
1.000 0.3864 0.01219 0.00446 -0.0552 0.7400 1.0000
1.250 0.4107 0.01227 0.00442 -0.0543 0.7183 1.0000
1.500 0.4336 0.01239 0.00444 -0.0532 0.6956 1.0000
1.750 0.4570 0.01252 0.00445 -0.0520 0.6735 1.0000
2.000 0.4796 0.01267 0.00450 -0.0508 0.6501 1.0000
2.250 0.5025 0.01284 0.00456 -0.0496 0.6273 1.0000
2.500 0.5251 0.01303 0.00465 -0.0484 0.6035 1.0000
2.750 0.5478 0.01323 0.00475 -0.0472 0.5804 1.0000
3.000 0.5704 0.01345 0.00488 -0.0460 0.5565 1.0000
3.250 0.5931 0.01370 0.00504 -0.0448 0.5329 1.0000
3.500 0.6157 0.01396 0.00520 -0.0436 0.5094 1.0000
3.750 0.6384 0.01423 0.00540 -0.0425 0.4856 1.0000
4.000 0.6609 0.01454 0.00562 -0.0414 0.4626 1.0000
4.250 0.6835 0.01485 0.00587 -0.0403 0.4389 1.0000
4.500 0.7059 0.01519 0.00613 -0.0392 0.4163 1.0000
4.750 0.7284 0.01554 0.00642 -0.0381 0.3934 1.0000
5.000 0.7506 0.01592 0.00676 -0.0371 0.3716 1.0000
5.250 0.7729 0.01631 0.00711 -0.0360 0.3495 1.0000
5.750 0.8170 0.01717 0.00788 -0.0340 0.3078 1.0000
6.000 0.8387 0.01764 0.00833 -0.0329 0.2877 1.0000
6.250 0.8601 0.01814 0.00878 -0.0318 0.2687 1.0000
6.500 0.8816 0.01864 0.00929 -0.0308 0.2494 1.0000
6.750 0.9028 0.01919 0.00982 -0.0298 0.2317 1.0000
7.000 0.9235 0.01976 0.01040 -0.0287 0.2146 1.0000
7.250 0.9439 0.02037 0.01100 -0.0276 0.1988 1.0000
7.500 0.9639 0.02102 0.01164 -0.0264 0.1834 1.0000
7.750 0.9836 0.02169 0.01232 -0.0253 0.1692 1.0000
8.000 1.0030 0.02239 0.01305 -0.0241 0.1556 1.0000
8.250 1.0220 0.02313 0.01385 -0.0229 0.1430 1.0000
8.500 1.0405 0.02390 0.01469 -0.0216 0.1313 1.0000
8.750 1.0581 0.02474 0.01556 -0.0203 0.1204 1.0000
9.000 1.0743 0.02565 0.01648 -0.0188 0.1112 1.0000
9.500 1.1062 0.02754 0.01857 -0.0158 0.0939 1.0000
9.750 1.1192 0.02862 0.01966 -0.0141 0.0873 1.0000
10.000 1.1335 0.02969 0.02088 -0.0125 0.0805 1.0000
10.250 1.1442 0.03087 0.02209 -0.0105 0.0753 1.0000
10.500 1.1550 0.03210 0.02347 -0.0085 0.0706 1.0000
10.750 1.1636 0.03331 0.02479 -0.0064 0.0661 1.0000
11.000 1.1686 0.03477 0.02626 -0.0041 0.0628 1.0000
11.250 1.1770 0.03623 0.02795 -0.0022 0.0593 1.0000
11.500 1.1829 0.03779 0.02966 -0.0003 0.0560 1.0000
11.750 1.1866 0.03943 0.03138 0.0015 0.0535 1.0000
12.000 1.1888 0.04141 0.03341 0.0031 0.0512 1.0000
12.250 1.1920 0.04351 0.03578 0.0044 0.0489 1.0000
12.500 1.1932 0.04579 0.03825 0.0055 0.0468 1.0000
12.750 1.1930 0.04818 0.04078 0.0062 0.0450 1.0000
13.000 1.1916 0.05074 0.04345 0.0066 0.0435 1.0000
13.250 1.1897 0.05360 0.04636 0.0068 0.0420 1.0000
13.500 1.1836 0.05716 0.05021 0.0065 0.0408 1.0000
13.750 1.1760 0.06114 0.05445 0.0057 0.0397 1.0000
14.000 1.1666 0.06554 0.05909 0.0044 0.0387 1.0000
14.250 1.1554 0.07040 0.06416 0.0025 0.0379 1.0000
14.500 1.1426 0.07575 0.06971 0.0000 0.0372 1.0000
14.750 1.1277 0.08175 0.07591 -0.0031 0.0366 1.0000
15.000 1.1096 0.08865 0.08300 -0.0069 0.0363 1.0000
15.250 1.0875 0.09681 0.09135 -0.0118 0.0361 1.0000
15.500 1.0441 0.11045 0.10525 -0.0204 0.0372 1.0000
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Polar data table (+)
Polar graphs
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