SA7025 (sa7025-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7025 (sa7025-il) Reynolds number: 100,000 Max Cl/Cd: 60.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7025-il-100000-n5.txt Download as CSV file: xf-sa7025-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SA7025
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3576 0.09321 0.08863 -0.0329 1.0000 0.0515
-7.500 -0.3729 0.09205 0.08759 -0.0318 1.0000 0.0521
-7.250 -0.3848 0.09025 0.08589 -0.0325 1.0000 0.0524
-7.000 -0.3909 0.08782 0.08352 -0.0344 1.0000 0.0527
-6.750 -0.3935 0.08481 0.08054 -0.0366 1.0000 0.0528
-6.500 -0.3931 0.08145 0.07716 -0.0390 1.0000 0.0530
-6.250 -0.3932 0.07733 0.07312 -0.0380 1.0000 0.0534
-6.000 -0.3814 0.07311 0.06893 -0.0378 0.9972 0.0543
-5.500 -0.3318 0.06205 0.05767 -0.0471 0.9873 0.0358
-5.250 -0.2896 0.05219 0.04740 -0.0592 0.9820 0.0269
-5.000 -0.2632 0.04730 0.04229 -0.0636 0.9760 0.0258
-4.750 -0.2298 0.04195 0.03659 -0.0689 0.9715 0.0246
-4.500 -0.1972 0.03715 0.03135 -0.0729 0.9667 0.0237
-4.250 -0.1645 0.03286 0.02646 -0.0757 0.9615 0.0229
-4.000 -0.1281 0.02917 0.02213 -0.0784 0.9578 0.0224
-3.750 -0.0946 0.02642 0.01881 -0.0800 0.9534 0.0222
-3.500 -0.0624 0.02444 0.01637 -0.0810 0.9480 0.0233
-3.250 -0.0260 0.02295 0.01448 -0.0826 0.9442 0.0257
-3.000 0.0066 0.02167 0.01287 -0.0833 0.9390 0.0273
-2.750 0.0392 0.02042 0.01142 -0.0840 0.9335 0.0278
-2.500 0.0759 0.01908 0.00993 -0.0857 0.9299 0.0291
-2.250 0.1050 0.01825 0.00900 -0.0859 0.9228 0.0313
-2.000 0.1403 0.01759 0.00820 -0.0872 0.9177 0.0350
-1.750 0.1720 0.01696 0.00750 -0.0877 0.9112 0.0461
-1.500 0.2033 0.01583 0.00708 -0.0888 0.9049 0.2104
-1.250 0.2300 0.01435 0.00709 -0.0888 0.8993 0.6003
-1.000 0.2685 0.01344 0.00681 -0.0895 0.8933 1.0000
-0.750 0.3036 0.01338 0.00647 -0.0906 0.8871 1.0000
-0.500 0.3315 0.01338 0.00625 -0.0904 0.8772 1.0000
-0.250 0.3603 0.01336 0.00606 -0.0904 0.8678 1.0000
0.000 0.3935 0.01328 0.00581 -0.0911 0.8606 1.0000
0.250 0.4202 0.01328 0.00569 -0.0906 0.8493 1.0000
0.500 0.4478 0.01326 0.00556 -0.0903 0.8382 1.0000
0.750 0.4761 0.01323 0.00543 -0.0901 0.8270 1.0000
1.000 0.5046 0.01319 0.00530 -0.0898 0.8153 1.0000
1.250 0.5328 0.01316 0.00519 -0.0896 0.8029 1.0000
1.500 0.5605 0.01314 0.00512 -0.0892 0.7894 1.0000
1.750 0.5880 0.01313 0.00506 -0.0888 0.7749 1.0000
2.000 0.6154 0.01314 0.00502 -0.0883 0.7595 1.0000
2.250 0.6431 0.01315 0.00499 -0.0879 0.7432 1.0000
2.500 0.6709 0.01317 0.00498 -0.0875 0.7261 1.0000
2.750 0.6979 0.01323 0.00500 -0.0870 0.7073 1.0000
3.000 0.7247 0.01332 0.00504 -0.0865 0.6873 1.0000
3.250 0.7513 0.01345 0.00511 -0.0859 0.6670 1.0000
3.500 0.7773 0.01362 0.00528 -0.0853 0.6454 1.0000
3.750 0.8029 0.01382 0.00544 -0.0846 0.6232 1.0000
4.000 0.8283 0.01405 0.00562 -0.0839 0.6006 1.0000
4.250 0.8530 0.01432 0.00585 -0.0831 0.5763 1.0000
4.500 0.8774 0.01462 0.00612 -0.0823 0.5518 1.0000
4.750 0.9014 0.01495 0.00647 -0.0815 0.5269 1.0000
5.000 0.9251 0.01531 0.00680 -0.0806 0.5018 1.0000
5.250 0.9483 0.01570 0.00716 -0.0797 0.4761 1.0000
5.500 0.9711 0.01613 0.00757 -0.0787 0.4495 1.0000
5.750 0.9933 0.01658 0.00801 -0.0777 0.4222 1.0000
6.000 1.0152 0.01708 0.00849 -0.0767 0.3948 1.0000
6.250 1.0366 0.01761 0.00908 -0.0756 0.3677 1.0000
6.500 1.0576 0.01817 0.00966 -0.0745 0.3402 1.0000
6.750 1.0779 0.01879 0.01027 -0.0733 0.3123 1.0000
7.000 1.0974 0.01947 0.01094 -0.0720 0.2829 1.0000
7.250 1.1163 0.02020 0.01167 -0.0707 0.2511 1.0000
7.500 1.1329 0.02109 0.01244 -0.0692 0.2126 1.0000
7.750 1.1472 0.02223 0.01336 -0.0676 0.1633 1.0000
8.000 1.1598 0.02362 0.01440 -0.0659 0.1100 1.0000
8.250 1.1720 0.02513 0.01562 -0.0641 0.0658 1.0000
8.500 1.1820 0.02688 0.01715 -0.0620 0.0349 1.0000
8.750 1.1914 0.02864 0.01894 -0.0595 0.0232 1.0000
9.000 1.1998 0.03038 0.02080 -0.0570 0.0190 1.0000
9.250 1.2047 0.03216 0.02276 -0.0541 0.0171 1.0000
9.500 1.2098 0.03381 0.02465 -0.0512 0.0160 1.0000
9.750 1.2136 0.03561 0.02667 -0.0485 0.0152 1.0000
10.000 1.2169 0.03751 0.02877 -0.0460 0.0146 1.0000
10.250 1.2200 0.03955 0.03100 -0.0436 0.0139 1.0000
10.500 1.2230 0.04169 0.03332 -0.0416 0.0133 1.0000
10.750 1.2254 0.04388 0.03573 -0.0399 0.0123 1.0000
11.000 1.2256 0.04642 0.03843 -0.0383 0.0117 1.0000
11.250 1.2224 0.04959 0.04177 -0.0368 0.0110 1.0000
11.500 1.2219 0.05269 0.04506 -0.0356 0.0107 1.0000
11.750 1.2223 0.05566 0.04830 -0.0348 0.0104 1.0000
12.000 1.2204 0.05908 0.05198 -0.0341 0.0101 1.0000
12.250 1.2164 0.06286 0.05602 -0.0339 0.0101 1.0000
12.500 1.2099 0.06706 0.06049 -0.0341 0.0100 1.0000
12.750 1.2014 0.07170 0.06538 -0.0349 0.0100 1.0000
13.000 1.1909 0.07682 0.07075 -0.0363 0.0099 1.0000
13.250 1.1788 0.08241 0.07659 -0.0384 0.0099 1.0000
13.500 1.1651 0.08862 0.08304 -0.0412 0.0100 1.0000
13.750 1.1502 0.09543 0.09006 -0.0448 0.0100 1.0000
14.000 1.1353 0.10272 0.09755 -0.0489 0.0101 1.0000
14.250 1.1194 0.11074 0.10575 -0.0538 0.0101 1.0000
14.500 1.1032 0.11939 0.11457 -0.0592 0.0102 1.0000
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Polar data table (+)
Polar graphs
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