Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf) Reynolds number: 100,000 Max Cl/Cd: 34.27 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-joukowsk0009-jf-100000-n5.txt Download as CSV file: xf-joukowsk0009-jf-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Joukovsky f=0% t=9%
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.8868 0.07102 0.06579 -0.0029 1.0000 0.0287
-11.000 -0.9305 0.06086 0.05526 -0.0116 1.0000 0.0280
-10.750 -0.9506 0.05607 0.05024 -0.0136 1.0000 0.0280
-10.500 -0.9611 0.05251 0.04647 -0.0135 1.0000 0.0282
-10.250 -0.9624 0.04931 0.04305 -0.0135 1.0000 0.0287
-10.000 -0.9579 0.04656 0.04009 -0.0133 1.0000 0.0294
-9.750 -0.9500 0.04405 0.03734 -0.0130 1.0000 0.0306
-9.500 -0.9405 0.04129 0.03424 -0.0126 1.0000 0.0320
-9.250 -0.9290 0.03831 0.03081 -0.0121 1.0000 0.0334
-9.000 -0.9142 0.03549 0.02750 -0.0115 1.0000 0.0346
-8.750 -0.8966 0.03302 0.02481 -0.0110 1.0000 0.0358
-8.500 -0.8767 0.03145 0.02315 -0.0106 1.0000 0.0377
-8.250 -0.8557 0.02998 0.02150 -0.0102 1.0000 0.0403
-8.000 -0.8338 0.02832 0.01953 -0.0096 1.0000 0.0430
-7.750 -0.8121 0.02659 0.01768 -0.0091 1.0000 0.0452
-7.500 -0.7898 0.02538 0.01645 -0.0087 1.0000 0.0486
-7.250 -0.7663 0.02424 0.01511 -0.0082 1.0000 0.0531
-7.000 -0.7437 0.02294 0.01377 -0.0077 1.0000 0.0570
-6.750 -0.7201 0.02194 0.01271 -0.0073 1.0000 0.0628
-6.500 -0.6965 0.02091 0.01164 -0.0069 1.0000 0.0696
-6.250 -0.6721 0.02004 0.01065 -0.0064 1.0000 0.0782
-6.000 -0.6481 0.01913 0.00978 -0.0061 1.0000 0.0892
-5.750 -0.6237 0.01828 0.00895 -0.0058 1.0000 0.1029
-5.500 -0.5990 0.01749 0.00822 -0.0055 1.0000 0.1211
-5.250 -0.5741 0.01675 0.00755 -0.0052 1.0000 0.1449
-5.000 -0.5490 0.01607 0.00698 -0.0050 1.0000 0.1744
-4.750 -0.5238 0.01543 0.00649 -0.0047 1.0000 0.2091
-4.500 -0.4984 0.01487 0.00607 -0.0045 1.0000 0.2474
-4.250 -0.4730 0.01437 0.00569 -0.0042 1.0000 0.2871
-4.000 -0.4475 0.01392 0.00538 -0.0038 1.0000 0.3273
-3.750 -0.4218 0.01353 0.00512 -0.0035 1.0000 0.3669
-3.500 -0.3963 0.01317 0.00488 -0.0030 1.0000 0.4050
-3.250 -0.3707 0.01287 0.00468 -0.0025 1.0000 0.4422
-3.000 -0.3453 0.01258 0.00453 -0.0020 1.0000 0.4771
-2.750 -0.3201 0.01233 0.00439 -0.0014 1.0000 0.5109
-2.500 -0.2950 0.01210 0.00426 -0.0007 1.0000 0.5435
-2.250 -0.2703 0.01190 0.00417 0.0000 1.0000 0.5749
-2.000 -0.2461 0.01172 0.00411 0.0009 1.0000 0.6053
-1.750 -0.2225 0.01156 0.00405 0.0018 1.0000 0.6348
-1.500 -0.1997 0.01142 0.00404 0.0028 0.9995 0.6637
-1.250 -0.1605 0.01137 0.00408 0.0008 0.9735 0.6960
-1.000 -0.1224 0.01133 0.00412 -0.0009 0.9481 0.7267
-0.750 -0.0866 0.01130 0.00416 -0.0020 0.9220 0.7560
-0.500 -0.0545 0.01128 0.00419 -0.0021 0.8948 0.7841
-0.250 -0.0260 0.01128 0.00421 -0.0013 0.8672 0.8116
0.000 0.0000 0.01128 0.00421 0.0000 0.8391 0.8392
0.250 0.0260 0.01128 0.00421 0.0013 0.8115 0.8672
0.500 0.0545 0.01128 0.00419 0.0021 0.7841 0.8948
0.750 0.0866 0.01130 0.00416 0.0019 0.7560 0.9220
1.000 0.1225 0.01133 0.00412 0.0009 0.7268 0.9481
1.250 0.1606 0.01137 0.00408 -0.0008 0.6960 0.9734
1.500 0.1997 0.01142 0.00404 -0.0029 0.6637 0.9995
1.750 0.2226 0.01156 0.00405 -0.0018 0.6348 1.0000
2.000 0.2462 0.01172 0.00411 -0.0009 0.6053 1.0000
2.250 0.2704 0.01190 0.00417 -0.0001 0.5749 1.0000
2.500 0.2951 0.01210 0.00426 0.0007 0.5435 1.0000
2.750 0.3202 0.01233 0.00439 0.0013 0.5109 1.0000
3.000 0.3454 0.01258 0.00453 0.0020 0.4771 1.0000
3.250 0.3708 0.01287 0.00469 0.0025 0.4421 1.0000
3.500 0.3964 0.01318 0.00488 0.0030 0.4049 1.0000
3.750 0.4219 0.01353 0.00512 0.0034 0.3669 1.0000
4.000 0.4475 0.01392 0.00539 0.0038 0.3273 1.0000
4.250 0.4730 0.01437 0.00569 0.0042 0.2871 1.0000
4.500 0.4984 0.01487 0.00607 0.0045 0.2474 1.0000
4.750 0.5238 0.01543 0.00649 0.0047 0.2091 1.0000
5.000 0.5490 0.01607 0.00698 0.0050 0.1744 1.0000
5.250 0.5741 0.01675 0.00755 0.0052 0.1450 1.0000
5.500 0.5990 0.01749 0.00822 0.0055 0.1211 1.0000
5.750 0.6236 0.01828 0.00895 0.0058 0.1029 1.0000
6.000 0.6481 0.01913 0.00977 0.0061 0.0892 1.0000
6.250 0.6721 0.02003 0.01064 0.0064 0.0781 1.0000
6.500 0.6964 0.02091 0.01164 0.0069 0.0696 1.0000
6.750 0.7199 0.02194 0.01271 0.0073 0.0627 1.0000
7.000 0.7435 0.02293 0.01377 0.0078 0.0571 1.0000
7.250 0.7661 0.02424 0.01511 0.0083 0.0531 1.0000
7.500 0.7896 0.02539 0.01646 0.0088 0.0487 1.0000
7.750 0.8119 0.02658 0.01767 0.0091 0.0452 1.0000
8.000 0.8335 0.02831 0.01953 0.0097 0.0430 1.0000
8.250 0.8553 0.02997 0.02149 0.0103 0.0404 1.0000
8.500 0.8760 0.03144 0.02315 0.0108 0.0377 1.0000
8.750 0.8957 0.03299 0.02478 0.0111 0.0358 1.0000
9.000 0.9132 0.03545 0.02745 0.0117 0.0346 1.0000
9.250 0.9281 0.03826 0.03075 0.0123 0.0334 1.0000
9.500 0.9396 0.04122 0.03416 0.0128 0.0320 1.0000
9.750 0.9492 0.04395 0.03723 0.0132 0.0306 1.0000
10.000 0.9563 0.04663 0.04017 0.0135 0.0295 1.0000
10.250 0.9616 0.04919 0.04292 0.0137 0.0287 1.0000
10.500 0.9601 0.05244 0.04640 0.0138 0.0282 1.0000
10.750 0.9487 0.05609 0.05027 0.0138 0.0281 1.0000
11.000 0.9290 0.06087 0.05528 0.0117 0.0281 1.0000
11.250 0.8873 0.07073 0.06549 0.0033 0.0286 1.0000
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