UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sfm-il) Reynolds number: 1,000,000 Max Cl/Cd: 291.04 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua79sfm-il-1000000.txt Download as CSV file: xf-ua79sfm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.1320 0.08526 0.08359 -0.0856 -0.0016 4.4222
-13.250 -0.1287 0.07997 0.07830 -0.0876 -0.0016 4.4224
-13.000 -0.1273 0.07509 0.07343 -0.0896 -0.0015 4.4228
-12.750 -0.1222 0.07181 0.07015 -0.0912 -0.0015 4.4233
-12.500 -0.1188 0.06810 0.06644 -0.0930 -0.0014 4.4236
-12.250 -0.1161 0.06453 0.06288 -0.0949 -0.0014 4.4240
-12.000 -0.1165 0.06045 0.05879 -0.0972 -0.0013 4.4244
-11.750 -0.1192 0.05620 0.05455 -0.0997 -0.0012 4.4248
-11.500 -0.1316 0.04984 0.04820 -0.1037 -0.0011 4.4246
-10.250 -0.2866 0.02638 0.02380 -0.1159 -0.0003 4.4232
-10.000 -0.2833 0.02511 0.02246 -0.1153 -0.0002 4.4235
-9.750 -0.2774 0.02413 0.02140 -0.1147 -0.0002 4.4241
-9.500 -0.2698 0.02309 0.02027 -0.1140 -0.0001 4.4249
-9.250 -0.2719 0.02015 0.01681 -0.1121 -0.0001 4.4307
-9.000 -0.2567 0.01913 0.01579 -0.1117 0.0000 4.4316
-8.750 -0.2477 0.01811 0.01442 -0.1104 0.0000 4.4376
-8.500 -0.2305 0.01718 0.01355 -0.1099 0.0000 4.4388
-8.250 -0.2165 0.01651 0.01273 -0.1090 0.0000 4.4443
-7.750 -0.1855 0.01553 0.01167 -0.1073 -0.0001 4.4508
-7.500 -0.1704 0.01505 0.01102 -0.1064 -0.0002 4.4550
-7.250 -0.1517 0.01440 0.01032 -0.1059 -0.0003 4.4565
-7.000 -0.1319 0.01368 0.00955 -0.1054 -0.0003 4.4572
-6.750 -0.1118 0.01296 0.00878 -0.1049 -0.0004 4.4573
-6.250 -0.0605 0.00954 0.00492 -0.1025 -0.0004 4.4518
-6.000 -0.0377 0.00857 0.00394 -0.1018 -0.0004 4.4477
-5.750 -0.0159 0.00823 0.00353 -0.1011 -0.0004 4.4433
-5.500 -0.0127 0.00794 0.00331 -0.0980 -0.0002 4.4417
-5.250 0.0078 0.00755 0.00288 -0.0973 0.0000 4.4385
-5.000 0.0306 0.00735 0.00265 -0.0969 0.0001 4.4369
-4.750 0.0519 0.00693 0.00222 -0.0964 0.0002 4.4357
-4.500 0.0743 0.00662 0.00190 -0.0959 0.0003 4.4344
-4.250 0.0970 0.00638 0.00164 -0.0956 0.0005 4.4333
-4.000 0.1201 0.00616 0.00141 -0.0952 0.0006 4.4325
-3.750 0.1435 0.00599 0.00121 -0.0949 0.0007 4.4320
-3.500 0.1468 0.00617 0.00140 -0.0916 0.0033 4.4320
-3.250 0.1691 0.00600 0.00121 -0.0911 0.0039 4.4321
-3.000 0.1921 0.00584 0.00103 -0.0907 0.0043 4.4330
-2.750 0.2156 0.00569 0.00087 -0.0904 0.0047 4.4354
-2.500 0.2338 0.00493 0.00076 -0.0900 0.0051 4.0354
-2.250 0.2467 0.00397 0.00082 -0.0891 0.0055 2.9443
-2.000 0.2756 0.00391 0.00122 -0.0890 0.0057 2.2997
-1.750 0.3097 0.00421 0.00150 -0.0893 0.0059 2.2085
-1.500 0.3409 0.00443 0.00170 -0.0895 0.0060 2.1667
-1.250 0.3434 0.00489 0.00218 -0.0858 0.0112 2.1553
-1.000 0.3716 0.00485 0.00211 -0.0859 0.0117 2.1521
-0.750 0.4005 0.00475 0.00200 -0.0862 0.0122 2.1488
-0.500 0.4295 0.00465 0.00187 -0.0864 0.0126 2.1451
-0.250 0.4585 0.00454 0.00175 -0.0868 0.0130 2.1410
0.000 0.4879 0.00443 0.00162 -0.0871 0.0134 2.1363
0.250 0.5173 0.00431 0.00149 -0.0875 0.0138 2.1307
0.500 0.5456 0.00421 0.00138 -0.0877 0.0142 2.1244
0.750 0.5742 0.00409 0.00126 -0.0881 0.0147 2.1175
1.000 0.6037 0.00394 0.00110 -0.0885 0.0151 2.1093
1.250 0.6334 0.00378 0.00093 -0.0890 0.0157 2.0994
1.500 0.6372 0.00411 0.00131 -0.0856 0.0216 2.0817
1.750 0.6624 0.00399 0.00118 -0.0855 0.0232 2.0689
2.000 0.6932 0.00371 0.00090 -0.0862 0.0243 2.0661
2.250 0.7241 0.00344 0.00064 -0.0869 0.0254 2.0632
2.500 0.7537 0.00323 0.00043 -0.0874 0.0265 2.0600
2.750 0.7666 0.00330 0.00054 -0.0853 0.0309 2.0555
3.000 0.7843 0.00327 0.00054 -0.0840 0.0346 2.0506
3.250 0.8109 0.00312 0.00041 -0.0841 0.0366 2.0457
3.500 0.8411 0.00289 0.00019 -0.0847 0.0387 2.0405
3.750 0.8316 0.00295 0.00028 -0.0788 0.0533 2.0313
4.000 0.8078 0.00324 0.00061 -0.0709 0.0723 2.0210
4.250 0.8223 0.00307 0.00037 -0.0689 0.1139 2.0145
4.500 0.8444 0.00297 0.00023 -0.0683 0.1428 2.0093
4.750 0.8317 0.00329 0.00048 -0.0623 0.2291 2.0029
5.000 0.8086 0.00367 0.00064 -0.0552 0.3673 2.0009
5.250 0.7921 0.00396 0.00079 -0.0495 0.4835 2.0009
5.500 0.7743 0.00431 0.00103 -0.0437 0.6153 2.0009
5.750 0.7495 0.00481 0.00134 -0.0372 0.7970 2.0009
6.000 0.7328 0.00523 0.00161 -0.0319 0.9651 2.0009
6.250 0.7121 0.00575 0.00191 -0.0263 1.2333 2.0009
6.500 0.6859 0.00643 0.00222 -0.0203 1.6727 2.0009
6.750 0.6682 0.00701 0.00244 -0.0155 2.1425 2.0009
7.000 0.6476 0.00772 0.00275 -0.0107 2.7833 2.0009
7.250 0.6211 0.00870 0.00325 -0.0055 4.0002 2.0009
7.500 0.6247 0.00888 0.00342 -0.0032 4.2690 2.0009
7.750 0.6302 0.00898 0.00357 -0.0011 4.2782 2.0009
8.000 0.6357 0.00910 0.00374 0.0009 4.2823 2.0009
8.250 0.6410 0.00923 0.00392 0.0029 4.2841 2.0009
8.500 0.6456 0.00937 0.00410 0.0049 4.2849 2.0009
8.750 0.6503 0.00952 0.00431 0.0069 4.2852 2.0009
9.000 0.6536 0.00971 0.00454 0.0090 4.2854 2.0009
9.250 0.6565 0.00991 0.00480 0.0111 4.2850 2.0009
9.500 0.6581 0.01017 0.00511 0.0132 4.2844 2.0009
9.750 0.6590 0.01044 0.00543 0.0154 4.2837 2.0009
10.000 0.6606 0.01070 0.00574 0.0174 4.2826 2.0009
10.250 0.6636 0.01091 0.00600 0.0193 4.2811 2.0009
10.500 0.6666 0.01112 0.00625 0.0211 4.2790 2.0009
10.750 0.6674 0.01142 0.00661 0.0231 4.2742 2.0009
11.000 0.6667 0.01176 0.00702 0.0251 4.2697 2.0009
11.250 0.6645 0.01219 0.00751 0.0270 4.2657 2.0009
11.500 0.6596 0.01272 0.00810 0.0290 4.2621 2.0009
11.750 0.6508 0.01343 0.00886 0.0311 4.2589 2.0009
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Polar data table (+)
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