GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.85 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe198-il-1000000-n5.txt Download as CSV file: xf-goe198-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 198 (L.F.G. 5294) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2262 0.09938 0.09713 -0.0438 0.8487 0.0127
-8.750 -0.2178 0.09643 0.09418 -0.0454 0.8454 0.0130
-8.500 -0.2169 0.09110 0.08884 -0.0486 0.8413 0.0139
-8.250 -0.2060 0.08904 0.08677 -0.0497 0.8377 0.0141
-8.000 -0.1950 0.08699 0.08471 -0.0509 0.8343 0.0142
-7.750 -0.1842 0.08489 0.08262 -0.0523 0.8304 0.0144
-7.500 -0.1718 0.08255 0.08027 -0.0545 0.8256 0.0146
-7.250 -0.1575 0.07973 0.07742 -0.0575 0.8205 0.0149
-7.000 -0.1415 0.07671 0.07440 -0.0611 0.8155 0.0151
-6.750 -0.1240 0.07356 0.07121 -0.0650 0.8093 0.0154
-6.500 -0.1049 0.07029 0.06790 -0.0692 0.8031 0.0156
-6.250 -0.0799 0.06461 0.06217 -0.0777 0.7970 0.0168
-6.000 -0.0585 0.06247 0.06000 -0.0804 0.7909 0.0170
-5.750 -0.0350 0.06004 0.05753 -0.0838 0.7860 0.0172
-5.500 -0.0096 0.05738 0.05484 -0.0877 0.7803 0.0174
-5.250 0.0173 0.05453 0.05193 -0.0919 0.7738 0.0177
-5.000 0.0461 0.05153 0.04886 -0.0964 0.7675 0.0179
-4.750 0.0766 0.04840 0.04566 -0.1011 0.7594 0.0181
-4.500 0.1085 0.04525 0.04242 -0.1057 0.7517 0.0182
-4.250 0.1418 0.04215 0.03922 -0.1103 0.7426 0.0188
-4.000 0.1778 0.03857 0.03551 -0.1153 0.7344 0.0191
-3.750 0.2190 0.03404 0.03078 -0.1213 0.7253 0.0196
-3.500 0.2558 0.03056 0.02713 -0.1253 0.7150 0.0197
-3.250 0.2924 0.02708 0.02342 -0.1290 0.7020 0.0201
-3.000 0.3269 0.02432 0.02043 -0.1317 0.6848 0.0202
-2.750 0.3592 0.02238 0.01825 -0.1335 0.6608 0.0204
-2.500 0.3911 0.02065 0.01626 -0.1350 0.6321 0.0206
-2.250 0.4233 0.01887 0.01419 -0.1364 0.6053 0.0210
-2.000 0.4658 0.01239 0.00675 -0.1401 0.5871 0.0218
-1.750 0.4955 0.01165 0.00573 -0.1406 0.5694 0.0222
-1.500 0.5249 0.01112 0.00499 -0.1410 0.5560 0.0225
-1.250 0.5539 0.01075 0.00443 -0.1413 0.5396 0.0227
-1.000 0.5826 0.01052 0.00404 -0.1415 0.5228 0.0230
-0.750 0.6113 0.01035 0.00375 -0.1417 0.5110 0.0232
-0.500 0.6401 0.01021 0.00354 -0.1419 0.5014 0.0234
-0.250 0.6687 0.01013 0.00339 -0.1421 0.4910 0.0236
0.000 0.6974 0.00988 0.00304 -0.1423 0.4774 0.0241
0.250 0.7258 0.00983 0.00292 -0.1425 0.4614 0.0244
0.500 0.7542 0.00982 0.00284 -0.1426 0.4441 0.0248
0.750 0.7820 0.00989 0.00280 -0.1427 0.4171 0.0252
1.000 0.8081 0.01022 0.00287 -0.1425 0.3623 0.0255
1.250 0.8349 0.01046 0.00294 -0.1424 0.3316 0.0260
1.750 0.8904 0.01064 0.00302 -0.1425 0.3087 0.0273
2.000 0.9181 0.01074 0.00307 -0.1426 0.2990 0.0278
2.250 0.9459 0.01082 0.00311 -0.1426 0.2889 0.0284
2.500 0.9735 0.01091 0.00317 -0.1426 0.2789 0.0296
2.750 1.0008 0.01106 0.00326 -0.1426 0.2670 0.0307
3.000 1.0278 0.01123 0.00336 -0.1425 0.2521 0.0319
3.250 1.0538 0.01153 0.00353 -0.1423 0.2242 0.0335
3.750 1.0946 0.01353 0.00476 -0.1403 0.0586 0.0686
4.000 1.1210 0.01372 0.00495 -0.1401 0.0548 0.0740
4.250 1.1474 0.01390 0.00515 -0.1399 0.0535 0.0795
4.500 1.1736 0.01408 0.00534 -0.1397 0.0526 0.0836
4.750 1.1997 0.01427 0.00556 -0.1395 0.0517 0.0907
5.250 1.2476 0.01344 0.00627 -0.1386 0.0501 1.0000
5.500 1.2730 0.01371 0.00653 -0.1383 0.0494 1.0000
5.750 1.2981 0.01400 0.00681 -0.1379 0.0487 1.0000
6.000 1.3230 0.01429 0.00710 -0.1375 0.0480 1.0000
6.250 1.3475 0.01461 0.00741 -0.1370 0.0474 1.0000
6.500 1.3714 0.01496 0.00777 -0.1364 0.0463 1.0000
6.750 1.3955 0.01528 0.00809 -0.1359 0.0454 1.0000
7.000 1.4197 0.01556 0.00837 -0.1354 0.0450 1.0000
7.250 1.4435 0.01585 0.00868 -0.1348 0.0445 1.0000
7.500 1.4669 0.01617 0.00901 -0.1342 0.0440 1.0000
7.750 1.4900 0.01648 0.00934 -0.1336 0.0432 1.0000
8.000 1.5127 0.01681 0.00968 -0.1328 0.0424 1.0000
8.250 1.5348 0.01716 0.01004 -0.1320 0.0416 1.0000
8.500 1.5561 0.01753 0.01043 -0.1311 0.0406 1.0000
8.750 1.5764 0.01795 0.01084 -0.1300 0.0392 1.0000
9.000 1.5963 0.01836 0.01126 -0.1288 0.0381 1.0000
9.250 1.6168 0.01870 0.01163 -0.1277 0.0373 1.0000
9.500 1.6364 0.01907 0.01202 -0.1265 0.0359 1.0000
9.750 1.6543 0.01948 0.01244 -0.1250 0.0338 1.0000
10.000 1.6696 0.01996 0.01292 -0.1230 0.0314 1.0000
10.250 1.6788 0.02085 0.01367 -0.1203 0.0174 1.0000
10.500 1.6893 0.02174 0.01459 -0.1178 0.0145 1.0000
10.750 1.7011 0.02259 0.01548 -0.1156 0.0132 1.0000
11.000 1.7124 0.02351 0.01644 -0.1135 0.0121 1.0000
11.250 1.7251 0.02438 0.01736 -0.1117 0.0116 1.0000
11.500 1.7372 0.02532 0.01836 -0.1100 0.0111 1.0000
11.750 1.7483 0.02635 0.01944 -0.1081 0.0106 1.0000
12.000 1.7584 0.02749 0.02063 -0.1063 0.0101 1.0000
12.250 1.7672 0.02876 0.02196 -0.1044 0.0097 1.0000
12.500 1.7747 0.03016 0.02342 -0.1025 0.0092 1.0000
12.750 1.7833 0.03149 0.02483 -0.1007 0.0090 1.0000
13.000 1.7917 0.03288 0.02628 -0.0991 0.0087 1.0000
13.250 1.7991 0.03437 0.02784 -0.0975 0.0085 1.0000
13.500 1.8054 0.03600 0.02953 -0.0958 0.0082 1.0000
13.750 1.8107 0.03776 0.03137 -0.0942 0.0079 1.0000
14.000 1.8148 0.03969 0.03337 -0.0927 0.0077 1.0000
14.250 1.8175 0.04179 0.03555 -0.0912 0.0075 1.0000
14.500 1.8188 0.04410 0.03794 -0.0898 0.0073 1.0000
14.750 1.8188 0.04664 0.04056 -0.0884 0.0071 1.0000
15.000 1.8168 0.04953 0.04354 -0.0873 0.0069 1.0000
15.250 1.8157 0.05241 0.04652 -0.0863 0.0068 1.0000
15.500 1.8155 0.05530 0.04950 -0.0856 0.0067 1.0000
15.750 1.8142 0.05845 0.05275 -0.0851 0.0066 1.0000
16.000 1.8120 0.06180 0.05620 -0.0848 0.0065 1.0000
16.250 1.8084 0.06541 0.05992 -0.0846 0.0064 1.0000
16.500 1.8037 0.06928 0.06389 -0.0846 0.0063 1.0000
16.750 1.7982 0.07333 0.06805 -0.0848 0.0062 1.0000
17.000 1.7915 0.07764 0.07246 -0.0851 0.0061 1.0000
17.250 1.7839 0.08215 0.07708 -0.0856 0.0060 1.0000
17.500 1.7751 0.08683 0.08187 -0.0862 0.0060 1.0000
17.750 1.7658 0.09166 0.08680 -0.0870 0.0059 1.0000
18.000 1.7557 0.09665 0.09191 -0.0879 0.0058 1.0000
18.250 1.7453 0.10178 0.09714 -0.0890 0.0058 1.0000
18.500 1.7345 0.10700 0.10247 -0.0903 0.0057 1.0000
18.750 1.7234 0.11234 0.10791 -0.0917 0.0056 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)