UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-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 (ua79sf18-il) Reynolds number: 1,000,000 Max Cl/Cd: 133.27 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ua79sf18-il-1000000.txt Download as CSV file: xf-ua79sf18-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.0994 0.15332 0.15024 -0.1209 0.7833 0.0052
-16.500 -0.0933 0.14978 0.14670 -0.1226 0.7829 0.0052
-6.750 -0.1194 0.01853 0.01297 -0.1293 0.7636 0.0085
-6.500 -0.0943 0.01590 0.01016 -0.1284 0.7632 0.0054
-6.250 -0.0785 0.01517 0.00936 -0.1266 0.7626 0.0054
-6.000 -0.0605 0.01472 0.00887 -0.1252 0.7620 0.0053
-5.750 -0.0447 0.01416 0.00825 -0.1235 0.7614 0.0054
-5.500 -0.0263 0.01373 0.00777 -0.1223 0.7608 0.0055
-5.250 -0.0067 0.01334 0.00735 -0.1212 0.7602 0.0060
-5.000 0.0150 0.01304 0.00702 -0.1205 0.7597 0.0066
-4.750 0.0380 0.01280 0.00674 -0.1200 0.7592 0.0072
-4.500 0.0620 0.01260 0.00649 -0.1197 0.7587 0.0077
-4.250 0.0861 0.01239 0.00623 -0.1194 0.7582 0.0083
-4.000 0.1108 0.01220 0.00602 -0.1192 0.7577 0.0106
-3.750 0.1337 0.01188 0.00581 -0.1188 0.7572 0.0405
-3.500 0.1475 0.01086 0.00545 -0.1173 0.7566 0.2219
-3.250 0.1622 0.00977 0.00511 -0.1161 0.7559 0.4329
-3.000 0.1822 0.00943 0.00532 -0.1153 0.7550 0.6179
-2.750 0.2098 0.00977 0.00565 -0.1154 0.7544 0.6393
-2.500 0.2372 0.00998 0.00585 -0.1156 0.7537 0.6511
-2.250 0.2640 0.01023 0.00615 -0.1154 0.7527 0.6656
-2.000 0.2916 0.01034 0.00625 -0.1157 0.7515 0.6711
-1.750 0.3196 0.01043 0.00630 -0.1160 0.7504 0.6751
-1.500 0.3476 0.01040 0.00628 -0.1164 0.7494 0.6787
-1.250 0.3762 0.01044 0.00632 -0.1169 0.7485 0.6816
-1.000 0.4048 0.01047 0.00632 -0.1174 0.7476 0.6838
-0.750 0.4339 0.01048 0.00630 -0.1181 0.7468 0.6856
-0.500 0.4631 0.01050 0.00630 -0.1187 0.7461 0.6872
-0.250 0.4927 0.01053 0.00629 -0.1195 0.7454 0.6885
0.000 0.5226 0.01039 0.00614 -0.1203 0.7446 0.6901
0.250 0.5533 0.01028 0.00601 -0.1212 0.7438 0.6908
0.500 0.5844 0.01019 0.00590 -0.1223 0.7431 0.6911
0.750 0.6152 0.01017 0.00585 -0.1233 0.7422 0.6914
1.000 0.6430 0.01020 0.00588 -0.1238 0.7410 0.6916
1.250 0.6686 0.01015 0.00586 -0.1238 0.7392 0.6920
1.500 0.6960 0.01008 0.00581 -0.1241 0.7372 0.6925
1.750 0.7252 0.00995 0.00569 -0.1247 0.7355 0.6930
2.000 0.7562 0.00975 0.00549 -0.1257 0.7338 0.6932
2.250 0.7880 0.00951 0.00524 -0.1268 0.7323 0.6936
2.500 0.8213 0.00926 0.00498 -0.1283 0.7308 0.6942
2.750 0.8545 0.00908 0.00478 -0.1297 0.7293 0.6949
3.000 0.8808 0.00907 0.00480 -0.1298 0.7275 0.6954
3.250 0.9057 0.00906 0.00486 -0.1297 0.7254 0.6956
3.500 0.9325 0.00901 0.00484 -0.1299 0.7234 0.6957
3.750 0.9621 0.00882 0.00467 -0.1306 0.7209 0.6958
4.000 0.9906 0.00813 0.00395 -0.1307 0.7101 0.6959
4.250 1.0185 0.00787 0.00366 -0.1309 0.7025 0.6960
4.500 1.0328 0.00775 0.00357 -0.1284 0.6788 0.6962
4.750 1.0173 0.00801 0.00353 -0.1194 0.6275 0.6964
5.000 0.9912 0.00881 0.00415 -0.1090 0.5837 0.6966
5.250 0.9464 0.01067 0.00579 -0.0964 0.5444 0.6968
5.500 0.9479 0.01159 0.00668 -0.0926 0.5296 0.6970
5.750 0.9049 0.01414 0.00892 -0.0818 0.4711 0.6972
6.000 0.8892 0.01577 0.01034 -0.0755 0.4315 0.6974
6.250 0.8596 0.01800 0.01216 -0.0674 0.3577 0.6976
6.750 0.8305 0.02169 0.01498 -0.0563 0.2045 0.6983
7.000 0.7987 0.02465 0.01712 -0.0489 0.0524 0.6984
7.250 0.8069 0.02572 0.01804 -0.0469 0.0081 0.6985
7.500 0.8249 0.02629 0.01863 -0.0462 0.0062 0.6986
7.750 0.8433 0.02684 0.01922 -0.0455 0.0054 0.6987
8.000 0.8607 0.02746 0.01988 -0.0447 0.0050 0.6988
8.250 0.8771 0.02815 0.02062 -0.0438 0.0045 0.6990
8.500 0.8938 0.02883 0.02134 -0.0430 0.0045 0.6992
8.750 0.9089 0.02961 0.02218 -0.0420 0.0042 0.6993
9.000 0.9235 0.03045 0.02307 -0.0409 0.0042 0.6995
9.250 0.9366 0.03141 0.02411 -0.0397 0.0042 0.6997
9.500 0.9499 0.03238 0.02513 -0.0385 0.0044 0.6999
9.750 0.9619 0.03345 0.02626 -0.0373 0.0046 0.7000
10.000 0.9684 0.03494 0.02784 -0.0354 0.0049 0.7002
10.250 0.9830 0.03588 0.02880 -0.0346 0.0055 0.7005
10.500 1.0065 0.03622 0.02923 -0.0344 0.0075 0.7007
13.500 1.1762 0.05206 0.04561 -0.0243 0.0051 0.7047
13.750 1.1792 0.05398 0.04766 -0.0230 0.0050 0.7052
14.000 1.1735 0.05625 0.05008 -0.0212 0.0050 0.7059
14.250 1.1733 0.05844 0.05241 -0.0200 0.0049 0.7065
14.500 1.1716 0.06078 0.05489 -0.0189 0.0047 0.7072
14.750 1.1707 0.06318 0.05740 -0.0181 0.0043 0.7080
15.000 1.1821 0.06506 0.05939 -0.0177 0.0043 0.7087
15.250 1.1872 0.06733 0.06177 -0.0172 0.0040 0.7095
15.500 1.1920 0.06970 0.06422 -0.0169 0.0036 0.7103
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Polar data table (+)
Polar graphs
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