UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il) Reynolds number: 50,000 Max Cl/Cd: 15.17 at α=11.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ua79sf18-il-50000-n5.txt Download as CSV file: xf-ua79sf18-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.1376 0.12408 0.11696 -0.1289 0.9162 0.0337
-12.500 -0.1516 0.12227 0.11524 -0.1264 0.9144 0.0336
-12.250 -0.1627 0.12045 0.11348 -0.1242 0.9123 0.0333
-12.000 -0.1745 0.11765 0.11075 -0.1231 0.9104 0.0333
-11.750 -0.1854 0.11503 0.10819 -0.1219 0.9089 0.0329
-11.500 -0.1975 0.11232 0.10555 -0.1207 0.9076 0.0326
-11.250 -0.2086 0.10878 0.10207 -0.1206 0.9062 0.0321
-11.000 -0.2186 0.10461 0.09792 -0.1213 0.9049 0.0311
-10.750 -0.2340 0.09941 0.09274 -0.1233 0.9035 0.0310
-10.500 -0.2617 0.09729 0.09069 -0.1198 0.9009 0.0301
-10.250 -0.2911 0.09487 0.08832 -0.1166 0.8983 0.0295
-10.000 -0.3178 0.09204 0.08550 -0.1145 0.8961 0.0285
-9.750 -0.3463 0.08894 0.08237 -0.1126 0.8940 0.0281
-9.500 -0.3743 0.08602 0.07939 -0.1104 0.8921 0.0272
-9.250 -0.4036 0.08354 0.07682 -0.1073 0.8907 0.0267
-9.000 -0.4340 0.08188 0.07508 -0.1027 0.8892 0.0265
-8.750 -0.4708 0.08117 0.07434 -0.0954 0.8868 0.0260
-8.500 -0.4998 0.07974 0.07283 -0.0895 0.8843 0.0260
-8.250 -0.5232 0.07764 0.07056 -0.0845 0.8824 0.0255
-8.000 -0.5404 0.07550 0.06823 -0.0802 0.8811 0.0256
-7.750 -0.5520 0.07335 0.06586 -0.0765 0.8799 0.0257
-7.500 -0.5586 0.07080 0.06301 -0.0733 0.8785 0.0257
-7.250 -0.5583 0.06832 0.06023 -0.0710 0.8770 0.0262
-7.000 -0.5607 0.06651 0.05820 -0.0677 0.8752 0.0273
-6.750 -0.5621 0.06452 0.05592 -0.0644 0.8739 0.0278
-6.500 -0.5589 0.06247 0.05354 -0.0615 0.8726 0.0284
-6.250 -0.5513 0.06053 0.05126 -0.0591 0.8708 0.0296
-6.000 -0.5387 0.05856 0.04885 -0.0572 0.8691 0.0307
-5.750 -0.5214 0.05670 0.04660 -0.0557 0.8674 0.0317
-5.500 -0.4994 0.05502 0.04455 -0.0547 0.8659 0.0327
-5.250 -0.4713 0.05353 0.04271 -0.0542 0.8642 0.0340
-5.000 -0.4502 0.05258 0.04150 -0.0525 0.8619 0.0351
-4.750 -0.4334 0.05147 0.04039 -0.0502 0.8594 0.0373
-4.500 -0.4175 0.05067 0.03951 -0.0481 0.8568 0.0406
-4.250 -0.3998 0.05004 0.03862 -0.0464 0.8542 0.0475
-4.000 -0.3830 0.04922 0.03780 -0.0452 0.8519 0.0591
-3.750 -0.3708 0.04823 0.03680 -0.0432 0.8494 0.0750
-3.500 -0.3682 0.04680 0.03571 -0.0400 0.8461 0.1085
-3.250 -0.3732 0.04327 0.03422 -0.0371 0.8433 0.3584
-3.000 -0.3742 0.04451 0.03648 -0.0286 0.8402 0.6630
-2.750 -0.3666 0.04647 0.03835 -0.0206 0.8375 0.7311
-2.500 -0.3710 0.04793 0.03982 -0.0107 0.8335 0.7772
-2.250 -0.3613 0.04935 0.04108 -0.0036 0.8300 0.8169
-2.000 -0.3346 0.05008 0.04148 -0.0023 0.8269 0.8348
-1.750 -0.3062 0.05051 0.04155 -0.0025 0.8243 0.8470
-1.500 -0.3005 0.05025 0.04110 0.0006 0.8194 0.8560
-1.250 -0.2799 0.05029 0.04078 0.0009 0.8155 0.8610
-1.000 -0.2532 0.05047 0.04068 0.0001 0.8122 0.8656
-0.750 -0.2449 0.05024 0.04027 0.0022 0.8075 0.8715
-0.500 -0.2240 0.05033 0.04016 0.0024 0.8030 0.8751
-0.250 -0.1976 0.05055 0.04015 0.0016 0.7995 0.8788
0.000 -0.1864 0.05045 0.03990 0.0032 0.7942 0.8829
0.250 -0.1686 0.05048 0.03977 0.0037 0.7893 0.8864
0.500 -0.1386 0.05085 0.03994 0.0022 0.7859 0.8888
0.750 -0.1269 0.05081 0.03980 0.0036 0.7795 0.8920
1.000 -0.1028 0.05104 0.03988 0.0030 0.7749 0.8951
1.250 -0.0835 0.05120 0.03986 0.0032 0.7697 0.8984
1.500 -0.0638 0.05140 0.03995 0.0033 0.7639 0.9012
1.750 -0.0325 0.05184 0.04027 0.0016 0.7602 0.9039
2.000 -0.0196 0.05196 0.04034 0.0026 0.7531 0.9075
2.250 0.0069 0.05233 0.04061 0.0017 0.7487 0.9108
2.500 0.0253 0.05261 0.04081 0.0018 0.7426 0.9140
2.750 0.0506 0.05300 0.04114 0.0008 0.7373 0.9166
3.000 0.0762 0.05342 0.04152 -0.0002 0.7324 0.9192
3.250 0.0959 0.05376 0.04184 -0.0004 0.7258 0.9221
3.500 0.1285 0.05425 0.04227 -0.0023 0.7221 0.9252
3.750 0.1434 0.05464 0.04268 -0.0020 0.7139 0.9288
4.000 0.1778 0.05514 0.04318 -0.0043 0.7097 0.9320
4.250 0.1945 0.05559 0.04365 -0.0044 0.7013 0.9359
4.500 0.2282 0.05602 0.04408 -0.0065 0.6965 0.9396
4.750 0.2480 0.05652 0.04465 -0.0071 0.6879 0.9435
5.000 0.2842 0.05696 0.04513 -0.0097 0.6830 0.9475
5.250 0.3036 0.05749 0.04574 -0.0103 0.6740 0.9529
5.500 0.3425 0.05788 0.04619 -0.0133 0.6696 0.9583
5.750 0.3619 0.05848 0.04687 -0.0141 0.6600 0.9666
6.000 0.3892 0.05891 0.04743 -0.0158 0.6525 0.9787
6.250 0.4167 0.05917 0.04776 -0.0171 0.6456 1.0000
6.500 0.4329 0.05966 0.04831 -0.0170 0.6366 1.0000
6.750 0.4635 0.05984 0.04856 -0.0184 0.6309 1.0000
7.000 0.4786 0.06047 0.04926 -0.0183 0.6205 1.0000
7.250 0.5135 0.06049 0.04945 -0.0201 0.6156 1.0000
7.500 0.5275 0.06125 0.05029 -0.0199 0.6044 1.0000
7.750 0.5457 0.06193 0.05107 -0.0201 0.5945 1.0000
8.000 0.5796 0.06188 0.05114 -0.0216 0.5890 1.0000
8.250 0.5950 0.06276 0.05213 -0.0216 0.5780 1.0000
8.500 0.6143 0.06347 0.05297 -0.0218 0.5681 1.0000
8.750 0.6471 0.06336 0.05302 -0.0230 0.5622 1.0000
9.000 0.6621 0.06435 0.05414 -0.0228 0.5508 1.0000
9.250 0.6818 0.06505 0.05508 -0.0229 0.5407 1.0000
9.500 0.7133 0.06482 0.05505 -0.0237 0.5340 1.0000
9.750 0.7286 0.06575 0.05615 -0.0234 0.5220 1.0000
10.000 0.7462 0.06650 0.05708 -0.0232 0.5107 1.0000
10.250 0.7734 0.06551 0.05629 -0.0226 0.4965 1.0000
10.500 0.8144 0.06130 0.05227 -0.0210 0.4750 1.0000
11.000 0.8540 0.05926 0.05047 -0.0177 0.4153 1.0000
11.250 0.8726 0.05972 0.05110 -0.0171 0.3967 1.0000
11.500 0.8943 0.05983 0.05136 -0.0165 0.3780 1.0000
11.750 0.9105 0.06003 0.05147 -0.0152 0.3375 1.0000
12.000 0.9221 0.06119 0.05261 -0.0143 0.3039 1.0000
12.250 0.9266 0.06293 0.05404 -0.0129 0.2483 1.0000
12.500 0.9228 0.06580 0.05646 -0.0117 0.1840 1.0000
12.750 0.9109 0.06984 0.05989 -0.0107 0.1122 1.0000
13.250 0.8880 0.07875 0.06790 -0.0099 0.0322 1.0000
13.500 0.8886 0.08206 0.07128 -0.0099 0.0274 1.0000
13.750 0.8880 0.08558 0.07486 -0.0101 0.0248 1.0000
14.000 0.8899 0.08887 0.07834 -0.0104 0.0228 1.0000
14.250 0.8915 0.09221 0.08196 -0.0108 0.0213 1.0000
14.500 0.8917 0.09582 0.08575 -0.0114 0.0201 1.0000
14.750 0.8922 0.09942 0.08952 -0.0121 0.0192 1.0000
15.000 0.8929 0.10302 0.09330 -0.0129 0.0187 1.0000
15.250 0.8921 0.10687 0.09732 -0.0138 0.0181 1.0000
15.500 0.8923 0.11058 0.10119 -0.0148 0.0177 1.0000
15.750 0.8938 0.11408 0.10484 -0.0157 0.0174 1.0000
16.000 0.8954 0.11751 0.10841 -0.0166 0.0171 1.0000
16.250 0.9000 0.12048 0.11150 -0.0173 0.0168 1.0000
16.500 0.9063 0.12318 0.11438 -0.0179 0.0166 1.0000
16.750 0.9136 0.12571 0.11710 -0.0185 0.0165 1.0000
17.000 0.9214 0.12822 0.11980 -0.0190 0.0163 1.0000
17.250 0.9289 0.13086 0.12265 -0.0197 0.0162 1.0000
17.500 0.9351 0.13382 0.12583 -0.0206 0.0160 1.0000
17.750 0.9393 0.13727 0.12953 -0.0218 0.0159 1.0000
18.000 0.9410 0.14132 0.13381 -0.0235 0.0159 1.0000
18.250 0.9403 0.14595 0.13867 -0.0257 0.0159 1.0000
18.500 0.9371 0.15124 0.14418 -0.0285 0.0159 1.0000
18.750 0.9326 0.15694 0.15008 -0.0317 0.0160 1.0000
19.000 0.9265 0.16327 0.15659 -0.0353 0.0161 1.0000
19.250 0.9200 0.16992 0.16341 -0.0393 0.0163 1.0000
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Polar data table (+)
Polar graphs
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