S8025 (8%) (s8025-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S8025 (8%) (s8025-il) Reynolds number: 50,000 Max Cl/Cd: 26.62 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s8025-il-50000-n5.txt Download as CSV file: xf-s8025-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S8025 (8%)
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6850 0.09662 0.08985 0.0113 1.0000 0.0362
-9.500 -0.6888 0.09055 0.08383 0.0078 1.0000 0.0360
-9.250 -0.6947 0.08406 0.07739 0.0034 1.0000 0.0357
-9.000 -0.7032 0.07776 0.07110 -0.0015 1.0000 0.0354
-8.750 -0.7157 0.07223 0.06555 -0.0052 1.0000 0.0351
-8.500 -0.7265 0.06656 0.05974 -0.0083 1.0000 0.0349
-8.250 -0.7329 0.06119 0.05414 -0.0104 1.0000 0.0348
-8.000 -0.7353 0.05583 0.04842 -0.0118 1.0000 0.0350
-7.750 -0.7320 0.05079 0.04289 -0.0125 1.0000 0.0354
-7.500 -0.7232 0.04615 0.03769 -0.0126 1.0000 0.0358
-7.250 -0.7100 0.04200 0.03309 -0.0124 1.0000 0.0367
-7.000 -0.6930 0.03896 0.02981 -0.0120 1.0000 0.0385
-6.750 -0.6737 0.03643 0.02696 -0.0115 1.0000 0.0423
-6.500 -0.6521 0.03358 0.02343 -0.0107 1.0000 0.0470
-6.250 -0.6309 0.03120 0.02101 -0.0100 1.0000 0.0519
-6.000 -0.6081 0.02912 0.01866 -0.0091 1.0000 0.0616
-5.750 -0.5854 0.02728 0.01673 -0.0083 1.0000 0.0752
-5.500 -0.5624 0.02565 0.01501 -0.0076 1.0000 0.0965
-5.250 -0.5393 0.02424 0.01359 -0.0069 1.0000 0.1249
-5.000 -0.5160 0.02300 0.01243 -0.0063 1.0000 0.1565
-4.750 -0.4920 0.02186 0.01129 -0.0057 1.0000 0.1899
-4.500 -0.4675 0.02083 0.01031 -0.0052 1.0000 0.2274
-4.250 -0.4429 0.01989 0.00949 -0.0047 1.0000 0.2717
-4.000 -0.4194 0.01907 0.00880 -0.0040 1.0000 0.3239
-3.750 -0.3963 0.01831 0.00820 -0.0030 1.0000 0.3815
-3.500 -0.3737 0.01763 0.00775 -0.0018 1.0000 0.4435
-3.250 -0.3514 0.01706 0.00738 -0.0003 1.0000 0.5100
-3.000 -0.3297 0.01656 0.00710 0.0015 1.0000 0.5769
-2.750 -0.3081 0.01613 0.00685 0.0036 1.0000 0.6425
-2.500 -0.2864 0.01576 0.00661 0.0059 1.0000 0.7062
-2.250 -0.2631 0.01545 0.00641 0.0079 1.0000 0.7688
-2.000 -0.2334 0.01521 0.00621 0.0088 1.0000 0.8313
-1.750 -0.1912 0.01503 0.00594 0.0070 1.0000 0.8934
-1.500 -0.1367 0.01487 0.00561 0.0023 1.0000 0.9477
-1.250 -0.0776 0.01465 0.00518 -0.0041 1.0000 0.9939
-1.000 -0.0543 0.01449 0.00492 -0.0042 1.0000 1.0000
-0.750 -0.0354 0.01438 0.00474 -0.0031 1.0000 1.0000
-0.500 -0.0162 0.01433 0.00464 -0.0021 1.0000 1.0000
-0.250 0.0031 0.01431 0.00459 -0.0011 1.0000 1.0000
0.000 0.0221 0.01433 0.00461 0.0000 1.0000 1.0000
0.250 0.0403 0.01441 0.00471 0.0011 1.0000 1.0000
0.500 0.0898 0.01457 0.00489 -0.0038 0.9498 1.0000
0.750 0.1427 0.01474 0.00504 -0.0085 0.8870 1.0000
1.000 0.1835 0.01494 0.00513 -0.0103 0.8241 1.0000
1.250 0.2118 0.01522 0.00522 -0.0095 0.7680 1.0000
1.500 0.2352 0.01554 0.00536 -0.0079 0.7182 1.0000
1.750 0.2579 0.01588 0.00550 -0.0062 0.6733 1.0000
2.000 0.2807 0.01623 0.00568 -0.0047 0.6318 1.0000
2.250 0.3040 0.01660 0.00588 -0.0034 0.5934 1.0000
2.500 0.3276 0.01698 0.00615 -0.0022 0.5568 1.0000
2.750 0.3516 0.01737 0.00641 -0.0012 0.5229 1.0000
3.000 0.3759 0.01778 0.00673 -0.0003 0.4899 1.0000
3.250 0.4004 0.01821 0.00708 0.0006 0.4584 1.0000
3.500 0.4249 0.01866 0.00749 0.0014 0.4284 1.0000
3.750 0.4496 0.01914 0.00792 0.0021 0.3998 1.0000
4.000 0.4745 0.01965 0.00840 0.0027 0.3727 1.0000
4.250 0.4997 0.02020 0.00897 0.0033 0.3468 1.0000
4.500 0.5248 0.02078 0.00952 0.0038 0.3229 1.0000
4.750 0.5498 0.02140 0.01019 0.0043 0.2987 1.0000
5.000 0.5746 0.02206 0.01088 0.0049 0.2755 1.0000
5.250 0.5989 0.02276 0.01162 0.0054 0.2541 1.0000
5.500 0.6233 0.02351 0.01246 0.0060 0.2322 1.0000
5.750 0.6472 0.02431 0.01329 0.0065 0.2125 1.0000
6.000 0.6711 0.02522 0.01427 0.0071 0.1944 1.0000
6.250 0.6948 0.02620 0.01539 0.0076 0.1761 1.0000
6.500 0.7180 0.02728 0.01663 0.0082 0.1599 1.0000
6.750 0.7408 0.02849 0.01796 0.0088 0.1453 1.0000
7.000 0.7631 0.02969 0.01929 0.0093 0.1310 1.0000
7.250 0.7851 0.03122 0.02102 0.0099 0.1193 1.0000
7.500 0.8060 0.03272 0.02271 0.0105 0.1076 1.0000
7.750 0.8268 0.03440 0.02446 0.0111 0.0997 1.0000
8.000 0.8462 0.03657 0.02709 0.0116 0.0913 1.0000
8.250 0.8639 0.03872 0.02951 0.0121 0.0838 1.0000
8.500 0.8805 0.04124 0.03236 0.0126 0.0783 1.0000
8.750 0.8970 0.04373 0.03494 0.0131 0.0746 1.0000
9.000 0.9026 0.04819 0.04014 0.0132 0.0709 1.0000
9.250 0.9081 0.05173 0.04406 0.0131 0.0669 1.0000
9.500 0.9217 0.05353 0.04585 0.0136 0.0631 1.0000
9.750 0.9162 0.05852 0.05121 0.0129 0.0620 1.0000
10.000 0.8997 0.06429 0.05733 0.0111 0.0617 1.0000
10.250 0.8771 0.07010 0.06330 0.0084 0.0618 1.0000
10.500 0.8537 0.07730 0.07055 0.0029 0.0622 1.0000
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Polar data table (+)
Polar graphs
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