SA7026 (sa7026-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7026 (sa7026-il) Reynolds number: 50,000 Max Cl/Cd: 40.58 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7026-il-50000-n5.txt Download as CSV file: xf-sa7026-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7026
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3600 0.10357 0.09726 -0.0348 1.0000 0.1106
-7.750 -0.3798 0.10288 0.09672 -0.0334 1.0000 0.1112
-7.500 -0.3956 0.10162 0.09560 -0.0324 1.0000 0.1115
-7.250 -0.3806 0.09708 0.09108 -0.0289 1.0000 0.1150
-7.000 -0.3865 0.09505 0.08913 -0.0268 1.0000 0.1171
-6.500 -0.4100 0.09140 0.08568 -0.0276 1.0000 0.1244
-6.000 -0.4053 0.07875 0.07288 -0.0364 1.0000 0.0564
-5.750 -0.4034 0.07587 0.07004 -0.0348 1.0000 0.0547
-5.500 -0.3996 0.07243 0.06660 -0.0353 1.0000 0.0526
-5.250 -0.3926 0.06814 0.06225 -0.0375 1.0000 0.0499
-5.000 -0.3599 0.05980 0.05335 -0.0479 0.9959 0.0440
-4.750 -0.3339 0.05542 0.04880 -0.0516 0.9909 0.0430
-4.500 -0.3036 0.05068 0.04372 -0.0562 0.9858 0.0420
-4.250 -0.2708 0.04621 0.03879 -0.0605 0.9812 0.0411
-4.000 -0.2382 0.04215 0.03419 -0.0638 0.9762 0.0405
-3.750 -0.2024 0.03857 0.02994 -0.0669 0.9720 0.0402
-3.500 -0.1682 0.03568 0.02644 -0.0690 0.9675 0.0402
-3.250 -0.1348 0.03326 0.02344 -0.0704 0.9626 0.0407
-3.000 -0.0990 0.03132 0.02097 -0.0719 0.9583 0.0416
-2.750 -0.0663 0.02993 0.01909 -0.0726 0.9532 0.0442
-2.500 -0.0350 0.02874 0.01781 -0.0737 0.9476 0.0499
-2.250 0.0012 0.02779 0.01652 -0.0750 0.9431 0.0562
-2.000 0.0301 0.02690 0.01545 -0.0753 0.9364 0.0638
-1.750 0.0670 0.02589 0.01444 -0.0771 0.9314 0.0990
-1.500 0.0982 0.02360 0.01421 -0.0789 0.9272 0.4792
-1.250 0.1266 0.02226 0.01392 -0.0772 0.9205 1.0000
-1.000 0.1635 0.02255 0.01358 -0.0792 0.9143 1.0000
-0.750 0.1929 0.02281 0.01343 -0.0798 0.9057 1.0000
-0.500 0.2254 0.02309 0.01335 -0.0810 0.8983 1.0000
-0.250 0.2581 0.02336 0.01330 -0.0822 0.8905 1.0000
0.000 0.2868 0.02364 0.01330 -0.0826 0.8815 1.0000
0.250 0.3241 0.02386 0.01328 -0.0845 0.8749 1.0000
0.750 0.3801 0.02438 0.01346 -0.0849 0.8558 1.0000
1.000 0.4153 0.02455 0.01348 -0.0863 0.8482 1.0000
1.250 0.4412 0.02482 0.01365 -0.0861 0.8377 1.0000
1.500 0.4711 0.02503 0.01377 -0.0866 0.8284 1.0000
1.750 0.5064 0.02512 0.01381 -0.0878 0.8206 1.0000
2.000 0.5318 0.02536 0.01400 -0.0874 0.8094 1.0000
2.250 0.5593 0.02554 0.01416 -0.0873 0.7987 1.0000
2.500 0.5910 0.02558 0.01420 -0.0876 0.7892 1.0000
2.750 0.6229 0.02557 0.01424 -0.0880 0.7795 1.0000
3.250 0.6760 0.02579 0.01452 -0.0871 0.7553 1.0000
3.500 0.7037 0.02583 0.01463 -0.0867 0.7433 1.0000
3.750 0.7322 0.02583 0.01476 -0.0863 0.7313 1.0000
4.000 0.7612 0.02579 0.01480 -0.0860 0.7190 1.0000
4.250 0.7898 0.02572 0.01484 -0.0856 0.7059 1.0000
4.500 0.8174 0.02568 0.01491 -0.0849 0.6917 1.0000
4.750 0.8446 0.02563 0.01506 -0.0842 0.6765 1.0000
5.000 0.8723 0.02555 0.01511 -0.0834 0.6605 1.0000
5.250 0.9011 0.02541 0.01510 -0.0828 0.6440 1.0000
5.500 0.9303 0.02527 0.01509 -0.0821 0.6267 1.0000
5.750 0.9534 0.02543 0.01540 -0.0808 0.6060 1.0000
6.000 0.9822 0.02534 0.01552 -0.0801 0.5859 1.0000
6.250 1.0045 0.02558 0.01590 -0.0787 0.5622 1.0000
6.500 1.0282 0.02577 0.01620 -0.0773 0.5373 1.0000
6.750 1.0511 0.02603 0.01656 -0.0759 0.5109 1.0000
7.000 1.0721 0.02642 0.01703 -0.0743 0.4828 1.0000
7.250 1.0913 0.02693 0.01769 -0.0725 0.4537 1.0000
7.500 1.1090 0.02754 0.01836 -0.0705 0.4239 1.0000
7.750 1.1246 0.02827 0.01911 -0.0684 0.3931 1.0000
8.000 1.1370 0.02914 0.02002 -0.0660 0.3608 1.0000
8.250 1.1470 0.03013 0.02103 -0.0633 0.3277 1.0000
8.500 1.1547 0.03124 0.02211 -0.0605 0.2958 1.0000
8.750 1.1597 0.03250 0.02338 -0.0575 0.2639 1.0000
9.000 1.1626 0.03397 0.02482 -0.0546 0.2313 1.0000
9.250 1.1629 0.03572 0.02645 -0.0517 0.1992 1.0000
9.500 1.1617 0.03778 0.02850 -0.0491 0.1638 1.0000
9.750 1.1580 0.04025 0.03077 -0.0467 0.1317 1.0000
10.250 1.1484 0.04620 0.03636 -0.0429 0.0756 1.0000
10.500 1.1443 0.04937 0.03943 -0.0415 0.0595 1.0000
10.750 1.1413 0.05262 0.04272 -0.0402 0.0496 1.0000
11.000 1.1382 0.05597 0.04610 -0.0391 0.0446 1.0000
11.250 1.1393 0.05911 0.04948 -0.0380 0.0392 1.0000
11.500 1.1381 0.06240 0.05286 -0.0374 0.0360 1.0000
11.750 1.1393 0.06571 0.05635 -0.0367 0.0331 1.0000
12.000 1.1432 0.06888 0.05984 -0.0360 0.0307 1.0000
12.250 1.1454 0.07232 0.06354 -0.0356 0.0289 1.0000
12.500 1.1472 0.07592 0.06739 -0.0353 0.0279 1.0000
12.750 1.1463 0.07990 0.07159 -0.0354 0.0270 1.0000
13.000 1.1435 0.08425 0.07616 -0.0359 0.0264 1.0000
13.250 1.1383 0.08901 0.08115 -0.0368 0.0260 1.0000
13.500 1.1308 0.09425 0.08662 -0.0383 0.0257 1.0000
13.750 1.1210 0.10003 0.09263 -0.0404 0.0255 1.0000
14.000 1.1089 0.10645 0.09929 -0.0433 0.0255 1.0000
14.250 1.0950 0.11363 0.10672 -0.0472 0.0256 1.0000
14.500 1.0788 0.12198 0.11532 -0.0521 0.0259 1.0000
14.750 1.0595 0.13201 0.12559 -0.0584 0.0264 1.0000
15.000 1.0358 0.14479 0.13855 -0.0665 0.0274 1.0000
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Polar data table (+)
Polar graphs
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