EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 393 AIRFOIL (e393-il) Reynolds number: 1,000,000 Max Cl/Cd: 152.69 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e393-il-1000000.txt Download as CSV file: xf-e393-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 393 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3321 0.11588 0.11424 -0.0380 1.0000 0.0087
-10.750 -0.3308 0.11253 0.11090 -0.0386 1.0000 0.0095
-8.500 -0.3776 0.02559 0.02285 -0.1162 0.9610 0.0075
-8.250 -0.3549 0.02237 0.01925 -0.1185 0.9504 0.0075
-8.000 -0.3304 0.01975 0.01626 -0.1200 0.9375 0.0075
-7.750 -0.3068 0.01718 0.01331 -0.1209 0.9202 0.0076
-7.500 -0.2832 0.01530 0.01110 -0.1212 0.9013 0.0078
-7.250 -0.2588 0.01429 0.00989 -0.1210 0.8820 0.0081
-7.000 -0.2345 0.01328 0.00865 -0.1207 0.8634 0.0082
-6.750 -0.2097 0.01246 0.00762 -0.1204 0.8461 0.0084
-6.500 -0.1843 0.01184 0.00684 -0.1201 0.8301 0.0087
-6.250 -0.1583 0.01131 0.00617 -0.1200 0.8152 0.0092
-6.000 -0.1319 0.01088 0.00560 -0.1198 0.8012 0.0099
-5.500 -0.0780 0.01022 0.00472 -0.1196 0.7756 0.0107
-5.250 -0.0512 0.00946 0.00379 -0.1197 0.7642 0.0119
-5.000 -0.0237 0.00917 0.00342 -0.1197 0.7536 0.0130
-4.750 0.0040 0.00896 0.00313 -0.1197 0.7437 0.0146
-4.500 0.0319 0.00864 0.00275 -0.1198 0.7340 0.0184
-4.250 0.0599 0.00851 0.00257 -0.1199 0.7252 0.0221
-3.750 0.1163 0.00806 0.00204 -0.1201 0.7089 0.0372
-3.500 0.1443 0.00787 0.00187 -0.1203 0.7014 0.0572
-3.250 0.1728 0.00762 0.00173 -0.1206 0.6942 0.0902
-3.000 0.2009 0.00741 0.00161 -0.1208 0.6874 0.1331
-2.750 0.2294 0.00714 0.00149 -0.1212 0.6808 0.1871
-2.500 0.2577 0.00692 0.00140 -0.1215 0.6743 0.2455
-2.250 0.2863 0.00667 0.00133 -0.1218 0.6684 0.3144
-2.000 0.3147 0.00645 0.00129 -0.1221 0.6624 0.3888
-1.750 0.3432 0.00633 0.00128 -0.1224 0.6567 0.4445
-1.500 0.3717 0.00626 0.00128 -0.1226 0.6509 0.4844
-1.250 0.4000 0.00627 0.00128 -0.1227 0.6455 0.5068
-1.000 0.4287 0.00625 0.00128 -0.1228 0.6401 0.5263
-0.750 0.4571 0.00624 0.00129 -0.1230 0.6346 0.5491
-0.500 0.4854 0.00626 0.00131 -0.1231 0.6294 0.5670
-0.250 0.5140 0.00625 0.00132 -0.1232 0.6242 0.5836
0.000 0.5423 0.00627 0.00134 -0.1233 0.6189 0.6007
0.250 0.5706 0.00628 0.00138 -0.1234 0.6139 0.6183
0.500 0.5991 0.00628 0.00141 -0.1236 0.6086 0.6355
0.750 0.6272 0.00631 0.00145 -0.1236 0.6033 0.6540
1.000 0.6555 0.00631 0.00150 -0.1238 0.5983 0.6739
1.250 0.6837 0.00631 0.00155 -0.1238 0.5928 0.6953
1.500 0.7115 0.00635 0.00162 -0.1238 0.5871 0.7182
1.750 0.7396 0.00633 0.00167 -0.1239 0.5807 0.7429
2.250 0.7947 0.00635 0.00182 -0.1238 0.5677 0.7958
2.500 0.8214 0.00637 0.00190 -0.1236 0.5610 0.8266
2.750 0.8476 0.00636 0.00198 -0.1232 0.5539 0.8617
3.000 0.8712 0.00635 0.00205 -0.1221 0.5469 0.9045
3.250 0.8952 0.00625 0.00207 -0.1212 0.5403 1.0000
3.500 0.9231 0.00637 0.00215 -0.1213 0.5322 1.0000
3.750 0.9512 0.00646 0.00223 -0.1214 0.5234 1.0000
4.000 0.9788 0.00658 0.00233 -0.1214 0.5152 1.0000
4.250 1.0066 0.00669 0.00244 -0.1215 0.5061 1.0000
4.500 1.0341 0.00681 0.00255 -0.1215 0.4963 1.0000
4.750 1.0611 0.00697 0.00267 -0.1215 0.4839 1.0000
5.000 1.0880 0.00713 0.00281 -0.1214 0.4726 1.0000
5.250 1.1146 0.00730 0.00296 -0.1213 0.4586 1.0000
5.500 1.1410 0.00750 0.00313 -0.1211 0.4428 1.0000
5.750 1.1656 0.00782 0.00333 -0.1207 0.4148 1.0000
6.000 1.1879 0.00832 0.00363 -0.1199 0.3691 1.0000
6.250 1.2082 0.00900 0.00404 -0.1188 0.3159 1.0000
6.500 1.2286 0.00967 0.00449 -0.1177 0.2703 1.0000
6.750 1.2482 0.01039 0.00498 -0.1166 0.2261 1.0000
7.000 1.2660 0.01122 0.00554 -0.1151 0.1785 1.0000
7.250 1.2844 0.01196 0.00607 -0.1138 0.1414 1.0000
7.500 1.3023 0.01270 0.00662 -0.1123 0.1077 1.0000
7.750 1.3207 0.01338 0.00716 -0.1110 0.0833 1.0000
8.000 1.3385 0.01406 0.00772 -0.1095 0.0630 1.0000
8.250 1.3565 0.01468 0.00827 -0.1081 0.0475 1.0000
8.500 1.3717 0.01545 0.00892 -0.1062 0.0312 1.0000
8.750 1.3829 0.01639 0.00974 -0.1036 0.0141 1.0000
9.000 1.3919 0.01723 0.01055 -0.1006 0.0075 1.0000
9.250 1.4049 0.01786 0.01122 -0.0982 0.0065 1.0000
9.500 1.4156 0.01863 0.01204 -0.0956 0.0055 1.0000
9.750 1.4253 0.01949 0.01298 -0.0929 0.0051 1.0000
10.000 1.4372 0.02024 0.01381 -0.0907 0.0049 1.0000
10.250 1.4479 0.02109 0.01474 -0.0884 0.0047 1.0000
10.500 1.4571 0.02207 0.01580 -0.0861 0.0045 1.0000
10.750 1.4658 0.02314 0.01694 -0.0839 0.0044 1.0000
11.000 1.4741 0.02428 0.01815 -0.0818 0.0042 1.0000
11.250 1.4816 0.02553 0.01948 -0.0798 0.0040 1.0000
11.500 1.4881 0.02693 0.02096 -0.0779 0.0039 1.0000
11.750 1.4940 0.02845 0.02256 -0.0761 0.0038 1.0000
12.000 1.4985 0.03018 0.02438 -0.0744 0.0037 1.0000
12.250 1.5021 0.03207 0.02637 -0.0728 0.0036 1.0000
12.500 1.5042 0.03419 0.02860 -0.0713 0.0035 1.0000
12.750 1.5060 0.03644 0.03094 -0.0701 0.0035 1.0000
13.000 1.5064 0.03892 0.03353 -0.0689 0.0034 1.0000
13.250 1.5058 0.04161 0.03633 -0.0680 0.0034 1.0000
13.500 1.5039 0.04455 0.03938 -0.0672 0.0033 1.0000
13.750 1.5009 0.04772 0.04267 -0.0666 0.0033 1.0000
14.000 1.4971 0.05112 0.04618 -0.0661 0.0032 1.0000
14.250 1.4915 0.05487 0.05005 -0.0659 0.0032 1.0000
14.500 1.4880 0.05849 0.05379 -0.0659 0.0032 1.0000
14.750 1.4795 0.06290 0.05835 -0.0660 0.0031 1.0000
15.000 1.4742 0.06707 0.06264 -0.0664 0.0031 1.0000
15.250 1.4678 0.07149 0.06719 -0.0670 0.0031 1.0000
15.500 1.4568 0.07677 0.07264 -0.0677 0.0030 1.0000
15.750 1.4494 0.08169 0.07771 -0.0688 0.0030 1.0000
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Polar data table (+)
Polar graphs
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