SD7090 (10%) (sd7090-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7090 (10%) (sd7090-il) Reynolds number: 200,000 Max Cl/Cd: 62.86 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7090-il-200000.txt Download as CSV file: xf-sd7090-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3814 0.09065 0.08718 -0.0264 1.0000 0.0657
-9.500 -0.3804 0.08698 0.08353 -0.0269 1.0000 0.0675
-9.250 -0.4904 0.08819 0.08460 -0.0293 1.0000 0.0638
-9.000 -0.4814 0.08614 0.08256 -0.0279 1.0000 0.0656
-8.750 -0.4820 0.08276 0.07922 -0.0288 1.0000 0.0672
-8.500 -0.4883 0.07877 0.07528 -0.0306 1.0000 0.0687
-8.250 -0.5027 0.07425 0.07084 -0.0333 1.0000 0.0698
-8.000 -0.5151 0.05569 0.05217 -0.0431 1.0000 0.0744
-7.750 -0.5179 0.04845 0.04502 -0.0427 1.0000 0.0757
-7.500 -0.5100 0.04534 0.04197 -0.0411 1.0000 0.0767
-7.250 -0.6048 0.03686 0.03149 -0.0381 1.0000 0.0403
-7.000 -0.5977 0.03276 0.02707 -0.0361 1.0000 0.0398
-6.750 -0.5865 0.02967 0.02359 -0.0341 1.0000 0.0398
-6.250 -0.5576 0.02464 0.01785 -0.0305 1.0000 0.0418
-6.000 -0.5394 0.02303 0.01608 -0.0290 1.0000 0.0430
-5.750 -0.5202 0.02162 0.01449 -0.0276 1.0000 0.0440
-5.500 -0.5003 0.02042 0.01313 -0.0261 1.0000 0.0454
-5.250 -0.4800 0.01938 0.01194 -0.0247 1.0000 0.0473
-5.000 -0.4595 0.01878 0.01116 -0.0233 1.0000 0.0499
-4.750 -0.4394 0.01738 0.00972 -0.0221 1.0000 0.0530
-4.500 -0.4190 0.01672 0.00907 -0.0209 1.0000 0.0566
-4.250 -0.3985 0.01618 0.00843 -0.0195 1.0000 0.0612
-4.000 -0.3757 0.01540 0.00774 -0.0190 0.9992 0.0698
-3.750 -0.3338 0.01478 0.00710 -0.0220 0.9940 0.0873
-3.500 -0.2941 0.01410 0.00656 -0.0248 0.9876 0.1094
-3.250 -0.2526 0.01360 0.00620 -0.0278 0.9818 0.1391
-3.000 -0.2137 0.01299 0.00583 -0.0304 0.9743 0.1902
-2.750 -0.1762 0.01218 0.00555 -0.0329 0.9671 0.2923
-2.500 -0.1386 0.01144 0.00533 -0.0351 0.9596 0.4214
-2.250 -0.1053 0.01078 0.00520 -0.0362 0.9505 0.5497
-2.000 -0.0675 0.01025 0.00513 -0.0377 0.9442 0.6740
-1.750 -0.0354 0.00991 0.00503 -0.0377 0.9343 0.7581
-1.500 0.0052 0.00962 0.00491 -0.0392 0.9293 0.8294
-1.250 0.0401 0.00945 0.00482 -0.0395 0.9192 0.8843
-1.000 0.0911 0.00935 0.00469 -0.0430 0.9141 0.9266
-0.750 0.1427 0.00931 0.00459 -0.0471 0.9038 0.9537
-0.500 0.1994 0.00923 0.00442 -0.0523 0.8933 0.9706
-0.250 0.2578 0.00912 0.00420 -0.0580 0.8799 0.9821
0.000 0.3138 0.00898 0.00396 -0.0635 0.8618 0.9926
0.250 0.3602 0.00885 0.00370 -0.0671 0.8402 1.0000
0.500 0.3813 0.00882 0.00355 -0.0657 0.8151 1.0000
0.750 0.4026 0.00883 0.00342 -0.0643 0.7920 1.0000
1.000 0.4226 0.00888 0.00335 -0.0626 0.7679 1.0000
1.250 0.4432 0.00896 0.00330 -0.0610 0.7451 1.0000
1.500 0.4637 0.00906 0.00329 -0.0594 0.7213 1.0000
1.750 0.4848 0.00918 0.00329 -0.0578 0.6984 1.0000
2.000 0.5059 0.00932 0.00331 -0.0563 0.6747 1.0000
2.250 0.5274 0.00947 0.00336 -0.0548 0.6510 1.0000
2.500 0.5489 0.00964 0.00341 -0.0534 0.6272 1.0000
2.750 0.5706 0.00982 0.00348 -0.0520 0.6027 1.0000
3.000 0.5923 0.01003 0.00357 -0.0506 0.5786 1.0000
3.250 0.6141 0.01024 0.00369 -0.0492 0.5537 1.0000
3.500 0.6359 0.01047 0.00382 -0.0479 0.5289 1.0000
3.750 0.6578 0.01074 0.00397 -0.0466 0.5046 1.0000
4.000 0.6798 0.01099 0.00415 -0.0453 0.4794 1.0000
4.250 0.7019 0.01128 0.00434 -0.0441 0.4553 1.0000
4.500 0.7240 0.01158 0.00454 -0.0429 0.4309 1.0000
4.750 0.7464 0.01189 0.00478 -0.0418 0.4068 1.0000
5.000 0.7683 0.01225 0.00504 -0.0406 0.3835 1.0000
5.250 0.7908 0.01258 0.00532 -0.0396 0.3595 1.0000
5.500 0.8127 0.01297 0.00561 -0.0385 0.3371 1.0000
5.750 0.8351 0.01334 0.00594 -0.0374 0.3142 1.0000
6.000 0.8567 0.01378 0.00629 -0.0364 0.2929 1.0000
6.250 0.8789 0.01419 0.00667 -0.0354 0.2711 1.0000
6.500 0.9004 0.01466 0.00706 -0.0343 0.2511 1.0000
6.750 0.9220 0.01515 0.00752 -0.0332 0.2318 1.0000
7.000 0.9436 0.01564 0.00798 -0.0322 0.2131 1.0000
7.250 0.9647 0.01617 0.00847 -0.0311 0.1957 1.0000
7.500 0.9853 0.01675 0.00900 -0.0300 0.1796 1.0000
7.750 1.0056 0.01737 0.00959 -0.0288 0.1643 1.0000
8.000 1.0257 0.01800 0.01020 -0.0277 0.1500 1.0000
8.250 1.0454 0.01866 0.01086 -0.0265 0.1367 1.0000
8.500 1.0648 0.01935 0.01157 -0.0252 0.1243 1.0000
8.750 1.0836 0.02011 0.01234 -0.0239 0.1131 1.0000
9.000 1.1011 0.02098 0.01321 -0.0224 0.1032 1.0000
9.250 1.1170 0.02202 0.01418 -0.0208 0.0942 1.0000
9.500 1.1355 0.02268 0.01498 -0.0194 0.0862 1.0000
9.750 1.1505 0.02383 0.01612 -0.0177 0.0795 1.0000
10.000 1.1668 0.02465 0.01704 -0.0162 0.0733 1.0000
10.250 1.1803 0.02600 0.01840 -0.0144 0.0681 1.0000
10.500 1.1952 0.02692 0.01947 -0.0127 0.0635 1.0000
10.750 1.2070 0.02814 0.02066 -0.0108 0.0595 1.0000
11.000 1.2185 0.02956 0.02222 -0.0087 0.0559 1.0000
11.250 1.2286 0.03063 0.02343 -0.0065 0.0527 1.0000
11.500 1.2372 0.03179 0.02461 -0.0044 0.0498 1.0000
11.750 1.2465 0.03385 0.02676 -0.0026 0.0469 1.0000
12.000 1.2519 0.03513 0.02827 -0.0003 0.0447 1.0000
12.250 1.2572 0.03657 0.02983 0.0017 0.0424 1.0000
12.500 1.2621 0.03802 0.03130 0.0034 0.0403 1.0000
12.750 1.2658 0.04084 0.03423 0.0049 0.0383 1.0000
13.000 1.2642 0.04277 0.03642 0.0066 0.0370 1.0000
13.250 1.2624 0.04503 0.03889 0.0079 0.0355 1.0000
13.500 1.2602 0.04748 0.04151 0.0088 0.0342 1.0000
13.750 1.2597 0.04975 0.04385 0.0092 0.0329 1.0000
14.000 1.2597 0.05246 0.04659 0.0094 0.0317 1.0000
14.250 1.2487 0.05694 0.05125 0.0093 0.0306 1.0000
14.500 1.2374 0.06097 0.05556 0.0084 0.0302 1.0000
14.750 1.2239 0.06567 0.06051 0.0069 0.0298 1.0000
15.000 1.2087 0.07090 0.06597 0.0047 0.0294 1.0000
15.250 1.1912 0.07691 0.07221 0.0018 0.0292 1.0000
15.500 1.1714 0.08368 0.07921 -0.0019 0.0292 1.0000
15.750 1.1487 0.09143 0.08716 -0.0066 0.0290 1.0000
16.000 1.1235 0.10025 0.09619 -0.0121 0.0293 1.0000
16.250 1.0945 0.11055 0.10668 -0.0187 0.0296 1.0000
16.500 1.0618 0.12237 0.11866 -0.0264 0.0302 1.0000
16.750 1.0257 0.13595 0.13238 -0.0349 0.0309 1.0000
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Polar data table (+)
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