S9027 (8%) (s9027-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S9027 (8%) (s9027-il) Reynolds number: 100,000 Max Cl/Cd: 32.76 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s9027-il-100000-n5.txt Download as CSV file: xf-s9027-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S9027 (8%)
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7907 0.08269 0.07764 -0.0008 1.0000 0.0325
-10.750 -0.8215 0.07083 0.06575 -0.0106 1.0000 0.0319
-10.500 -0.8506 0.06245 0.05723 -0.0180 1.0000 0.0315
-10.250 -0.8761 0.05712 0.05175 -0.0200 1.0000 0.0314
-10.000 -0.8946 0.05240 0.04673 -0.0199 1.0000 0.0314
-9.750 -0.9049 0.04772 0.04162 -0.0195 1.0000 0.0318
-9.500 -0.9070 0.04348 0.03688 -0.0186 1.0000 0.0323
-9.250 -0.9019 0.03998 0.03275 -0.0175 1.0000 0.0332
-9.000 -0.8896 0.03752 0.03020 -0.0168 1.0000 0.0348
-8.750 -0.8735 0.03587 0.02840 -0.0160 1.0000 0.0366
-8.500 -0.8575 0.03367 0.02588 -0.0151 1.0000 0.0383
-8.250 -0.8400 0.03136 0.02322 -0.0141 1.0000 0.0399
-8.000 -0.8207 0.02928 0.02078 -0.0131 1.0000 0.0418
-7.750 -0.8001 0.02750 0.01868 -0.0122 1.0000 0.0440
-7.500 -0.7797 0.02618 0.01732 -0.0115 1.0000 0.0473
-7.250 -0.7578 0.02499 0.01598 -0.0107 1.0000 0.0512
-7.000 -0.7352 0.02367 0.01439 -0.0098 1.0000 0.0549
-6.750 -0.7139 0.02239 0.01313 -0.0090 1.0000 0.0590
-6.500 -0.6910 0.02151 0.01213 -0.0082 1.0000 0.0658
-6.250 -0.6685 0.02058 0.01119 -0.0074 1.0000 0.0731
-6.000 -0.6453 0.01974 0.01020 -0.0066 1.0000 0.0815
-5.750 -0.6221 0.01902 0.00945 -0.0059 1.0000 0.0924
-5.500 -0.5989 0.01829 0.00873 -0.0052 1.0000 0.1041
-5.250 -0.5755 0.01762 0.00807 -0.0044 1.0000 0.1185
-5.000 -0.5519 0.01699 0.00745 -0.0037 1.0000 0.1337
-4.750 -0.5284 0.01638 0.00688 -0.0030 1.0000 0.1523
-4.500 -0.5047 0.01582 0.00638 -0.0022 1.0000 0.1736
-4.250 -0.4810 0.01530 0.00592 -0.0015 1.0000 0.1964
-4.000 -0.4573 0.01481 0.00553 -0.0007 1.0000 0.2249
-3.750 -0.4338 0.01433 0.00515 0.0000 1.0000 0.2570
-3.500 -0.4103 0.01388 0.00484 0.0009 1.0000 0.2937
-3.250 -0.3871 0.01344 0.00457 0.0017 1.0000 0.3361
-3.000 -0.3641 0.01302 0.00434 0.0027 1.0000 0.3815
-2.750 -0.3412 0.01262 0.00412 0.0037 1.0000 0.4300
-2.500 -0.3185 0.01224 0.00395 0.0049 1.0000 0.4812
-2.250 -0.2959 0.01189 0.00383 0.0061 1.0000 0.5366
-2.000 -0.2734 0.01156 0.00374 0.0074 1.0000 0.5954
-1.750 -0.2510 0.01127 0.00369 0.0089 1.0000 0.6570
-1.500 -0.2288 0.01103 0.00368 0.0106 1.0000 0.7183
-1.250 -0.2056 0.01085 0.00370 0.0122 1.0000 0.7792
-0.750 -0.1382 0.01074 0.00383 0.0111 1.0000 0.8977
-0.500 -0.0895 0.01077 0.00388 0.0072 1.0000 0.9445
-0.250 -0.0415 0.01079 0.00388 0.0031 1.0000 0.9802
0.000 0.0000 0.01078 0.00387 0.0000 1.0000 1.0000
0.250 0.0415 0.01079 0.00388 -0.0031 0.9803 1.0000
0.500 0.0895 0.01077 0.00387 -0.0072 0.9445 1.0000
0.750 0.1382 0.01074 0.00383 -0.0111 0.8977 1.0000
1.000 0.1777 0.01075 0.00376 -0.0128 0.8397 1.0000
1.250 0.2055 0.01085 0.00370 -0.0121 0.7796 1.0000
1.500 0.2287 0.01103 0.00368 -0.0106 0.7185 1.0000
1.750 0.2508 0.01127 0.00368 -0.0089 0.6569 1.0000
2.000 0.2732 0.01156 0.00374 -0.0074 0.5954 1.0000
2.250 0.2957 0.01189 0.00383 -0.0060 0.5368 1.0000
2.500 0.3182 0.01224 0.00395 -0.0048 0.4813 1.0000
2.750 0.3410 0.01262 0.00412 -0.0037 0.4302 1.0000
3.000 0.3639 0.01301 0.00433 -0.0026 0.3816 1.0000
3.250 0.3869 0.01344 0.00457 -0.0017 0.3364 1.0000
3.500 0.4101 0.01388 0.00484 -0.0008 0.2939 1.0000
3.750 0.4335 0.01433 0.00515 0.0000 0.2572 1.0000
4.000 0.4571 0.01480 0.00553 0.0008 0.2250 1.0000
4.250 0.4808 0.01530 0.00592 0.0015 0.1965 1.0000
4.500 0.5045 0.01582 0.00638 0.0023 0.1736 1.0000
4.750 0.5282 0.01638 0.00688 0.0030 0.1523 1.0000
5.000 0.5518 0.01699 0.00744 0.0037 0.1339 1.0000
5.250 0.5754 0.01762 0.00807 0.0045 0.1184 1.0000
5.500 0.5989 0.01828 0.00873 0.0052 0.1041 1.0000
5.750 0.6221 0.01902 0.00945 0.0059 0.0924 1.0000
6.000 0.6453 0.01975 0.01020 0.0066 0.0815 1.0000
6.250 0.6686 0.02059 0.01118 0.0074 0.0730 1.0000
6.500 0.6911 0.02151 0.01212 0.0082 0.0657 1.0000
6.750 0.7141 0.02240 0.01313 0.0089 0.0589 1.0000
7.000 0.7354 0.02367 0.01440 0.0098 0.0549 1.0000
7.250 0.7580 0.02499 0.01598 0.0107 0.0512 1.0000
7.500 0.7800 0.02619 0.01733 0.0115 0.0473 1.0000
7.750 0.8005 0.02750 0.01868 0.0121 0.0440 1.0000
8.000 0.8210 0.02930 0.02079 0.0131 0.0418 1.0000
8.250 0.8404 0.03139 0.02325 0.0140 0.0399 1.0000
8.500 0.8579 0.03369 0.02591 0.0150 0.0383 1.0000
8.750 0.8740 0.03589 0.02842 0.0159 0.0366 1.0000
9.000 0.8902 0.03753 0.03021 0.0167 0.0348 1.0000
9.250 0.9025 0.04001 0.03279 0.0174 0.0332 1.0000
9.500 0.9077 0.04353 0.03693 0.0185 0.0323 1.0000
9.750 0.9055 0.04779 0.04169 0.0193 0.0318 1.0000
10.000 0.8954 0.05247 0.04680 0.0197 0.0314 1.0000
10.250 0.8765 0.05725 0.05189 0.0198 0.0314 1.0000
10.500 0.8514 0.06258 0.05737 0.0177 0.0315 1.0000
10.750 0.8229 0.07088 0.06580 0.0104 0.0320 1.0000
11.000 0.7904 0.08321 0.07816 0.0002 0.0325 1.0000
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Polar data table (+)
Polar graphs
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