UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Reynolds number: 500,000 Max Cl/Cd: 65.03 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua79sf18-il-500000.txt Download as CSV file: xf-ua79sf18-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.0259 0.09544 0.09213 -0.1476 0.8033 0.0161
-12.000 -0.0278 0.09120 0.08792 -0.1493 0.8029 0.0166
-11.750 -0.0311 0.08669 0.08345 -0.1513 0.8025 0.0169
-11.500 -0.0365 0.08168 0.07847 -0.1537 0.8021 0.0171
-11.250 -0.0474 0.07486 0.07170 -0.1575 0.8016 0.0172
-11.000 -0.0701 0.06733 0.06414 -0.1621 0.8010 0.0168
-10.750 -0.0932 0.06233 0.05907 -0.1640 0.8002 0.0166
-10.500 -0.1151 0.05842 0.05509 -0.1643 0.7993 0.0167
-10.250 -0.1340 0.05531 0.05190 -0.1637 0.7986 0.0166
-10.000 -0.1523 0.05257 0.04907 -0.1622 0.7979 0.0165
-9.750 -0.1690 0.05019 0.04659 -0.1600 0.7970 0.0169
-9.500 -0.1844 0.04811 0.04439 -0.1570 0.7961 0.0173
-9.250 -0.1991 0.04663 0.04279 -0.1531 0.7953 0.0175
-9.000 -0.2121 0.04550 0.04155 -0.1486 0.7944 0.0179
-6.750 -0.1684 0.02743 0.02151 -0.1236 0.7849 0.0141
-6.500 -0.1390 0.02528 0.01919 -0.1234 0.7844 0.0107
-6.250 -0.1122 0.02331 0.01703 -0.1229 0.7839 0.0097
-6.000 -0.0920 0.02235 0.01597 -0.1216 0.7833 0.0094
-5.750 -0.0758 0.02168 0.01523 -0.1198 0.7826 0.0095
-5.500 -0.0611 0.02127 0.01475 -0.1178 0.7819 0.0097
-5.250 -0.0813 0.02236 0.01593 -0.1104 0.7753 0.0099
-5.000 -0.0708 0.02211 0.01563 -0.1077 0.7733 0.0104
-4.750 -0.0549 0.02175 0.01521 -0.1060 0.7720 0.0111
-4.500 -0.0353 0.02137 0.01477 -0.1048 0.7712 0.0118
-4.250 -0.0121 0.02110 0.01444 -0.1043 0.7705 0.0127
-4.000 -0.0552 0.02290 0.01627 -0.0928 0.7612 0.0124
-3.750 -0.0370 0.02254 0.01583 -0.0915 0.7595 0.0153
-3.500 -0.0094 0.02212 0.01535 -0.0917 0.7586 0.0183
-3.250 0.0119 0.02083 0.01460 -0.0912 0.7578 0.1558
-3.000 -0.0104 0.02112 0.01531 -0.0834 0.7510 0.2623
-2.750 0.0223 0.01950 0.01495 -0.0851 0.7523 0.6325
-2.500 0.0851 0.01919 0.01462 -0.0906 0.7562 0.6689
-2.250 0.0357 0.02086 0.01624 -0.0782 0.7444 0.6621
-2.000 0.0627 0.02123 0.01673 -0.0774 0.7438 0.6917
-1.750 0.0405 0.02289 0.01842 -0.0697 0.7355 0.6985
-1.500 0.0636 0.02314 0.01869 -0.0688 0.7337 0.7108
-1.250 0.0911 0.02325 0.01874 -0.0689 0.7326 0.7183
-1.000 0.1198 0.02326 0.01873 -0.0692 0.7319 0.7225
-0.750 0.1499 0.02323 0.01865 -0.0699 0.7312 0.7250
-0.500 0.1816 0.02316 0.01851 -0.0708 0.7307 0.7277
-0.250 0.2144 0.02305 0.01833 -0.0720 0.7303 0.7299
0.000 0.2477 0.02291 0.01813 -0.0733 0.7299 0.7312
0.250 0.2813 0.02271 0.01789 -0.0746 0.7296 0.7319
0.500 0.3166 0.02244 0.01758 -0.0762 0.7294 0.7323
0.750 0.3534 0.02208 0.01718 -0.0780 0.7292 0.7326
1.000 0.3909 0.02167 0.01673 -0.0799 0.7290 0.7330
1.250 0.4282 0.02127 0.01632 -0.0818 0.7288 0.7335
1.500 0.3795 0.02352 0.01857 -0.0703 0.7131 0.7347
1.750 0.4205 0.02305 0.01808 -0.0727 0.7143 0.7349
2.000 0.4594 0.02264 0.01766 -0.0748 0.7149 0.7351
2.250 0.4973 0.02226 0.01727 -0.0768 0.7154 0.7356
2.500 0.5357 0.02180 0.01682 -0.0788 0.7157 0.7366
2.750 0.5755 0.02121 0.01623 -0.0810 0.7159 0.7375
3.750 0.7383 0.01838 0.01346 -0.0904 0.7158 0.7387
4.000 0.7825 0.01766 0.01277 -0.0934 0.7160 0.7388
4.250 0.7381 0.01981 0.01492 -0.0823 0.7013 0.7393
4.500 0.7756 0.01924 0.01439 -0.0841 0.7015 0.7395
4.750 0.8138 0.01858 0.01377 -0.0860 0.7016 0.7397
6.000 0.9457 0.01546 0.01067 -0.0850 0.6486 0.7412
6.250 0.9644 0.01483 0.00950 -0.0827 0.5656 0.7415
6.500 0.9597 0.01593 0.01042 -0.0781 0.5368 0.7419
6.750 0.9321 0.01799 0.01214 -0.0701 0.4778 0.7424
7.000 0.9055 0.02024 0.01401 -0.0627 0.4182 0.7430
7.250 0.8941 0.02204 0.01551 -0.0578 0.3664 0.7436
7.500 0.8822 0.02400 0.01710 -0.0531 0.3032 0.7440
7.750 0.8707 0.02606 0.01866 -0.0487 0.2230 0.7444
8.000 0.8623 0.02807 0.02018 -0.0449 0.1419 0.7448
8.250 0.8411 0.03103 0.02239 -0.0396 0.0117 0.7451
8.500 0.8587 0.03167 0.02309 -0.0390 0.0090 0.7457
8.750 0.8753 0.03241 0.02389 -0.0382 0.0080 0.7462
9.000 0.8913 0.03320 0.02477 -0.0374 0.0075 0.7469
9.250 0.9064 0.03406 0.02573 -0.0365 0.0069 0.7476
9.500 0.9220 0.03489 0.02667 -0.0357 0.0069 0.7483
9.750 0.9366 0.03582 0.02769 -0.0348 0.0069 0.7491
10.000 0.9501 0.03685 0.02882 -0.0338 0.0069 0.7499
10.250 0.9638 0.03787 0.02993 -0.0329 0.0070 0.7510
10.500 0.9759 0.03905 0.03120 -0.0318 0.0071 0.7520
10.750 0.9867 0.04035 0.03260 -0.0307 0.0073 0.7530
11.000 0.9953 0.04187 0.03422 -0.0294 0.0075 0.7543
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Polar data table (+)
Polar graphs
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