GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Reynolds number: 500,000 Max Cl/Cd: 112.31 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe198-il-500000.txt Download as CSV file: xf-goe198-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.1610 0.09064 0.08816 -0.0569 0.9247 0.0223
-7.750 -0.1520 0.08814 0.08566 -0.0582 0.9186 0.0227
-7.500 -0.1436 0.08570 0.08320 -0.0594 0.9129 0.0232
-7.250 -0.1336 0.08320 0.08068 -0.0614 0.9080 0.0239
-7.000 -0.1174 0.08025 0.07771 -0.0661 0.9023 0.0249
-6.750 -0.0931 0.07698 0.07437 -0.0764 0.8964 0.0252
-6.500 -0.0683 0.07342 0.07075 -0.0837 0.8917 0.0252
-6.250 -0.0554 0.06973 0.06707 -0.0843 0.8869 0.0254
-6.000 -0.0421 0.06698 0.06430 -0.0839 0.8823 0.0256
-5.750 -0.0249 0.06443 0.06171 -0.0852 0.8781 0.0258
-5.500 -0.0041 0.06183 0.05910 -0.0878 0.8730 0.0262
-5.250 0.0190 0.05920 0.05644 -0.0910 0.8680 0.0268
-5.000 0.0447 0.05643 0.05360 -0.0948 0.8637 0.0276
-4.750 0.0742 0.05342 0.05053 -0.0995 0.8592 0.0287
-4.500 0.1338 0.04895 0.04583 -0.1125 0.8542 0.0298
-4.250 0.1547 0.04541 0.04226 -0.1143 0.8498 0.0301
-4.000 0.1763 0.04328 0.04008 -0.1151 0.8460 0.0305
-3.750 0.2024 0.04118 0.03796 -0.1169 0.8412 0.0309
-3.500 0.2315 0.03907 0.03580 -0.1193 0.8364 0.0317
-3.250 0.2634 0.03682 0.03345 -0.1221 0.8319 0.0329
-3.000 0.3171 0.03360 0.02987 -0.1282 0.8272 0.0353
-2.750 0.3433 0.03045 0.02669 -0.1302 0.8212 0.0359
-2.500 0.3698 0.02896 0.02514 -0.1312 0.8157 0.0365
-2.250 0.3993 0.02744 0.02356 -0.1325 0.8096 0.0376
-2.000 0.4326 0.02567 0.02165 -0.1342 0.8032 0.0399
-1.750 0.4718 0.02284 0.01846 -0.1365 0.7977 0.0426
-1.500 0.4999 0.02177 0.01740 -0.1374 0.7895 0.0435
-1.250 0.5295 0.02075 0.01626 -0.1381 0.7826 0.0457
-1.000 0.5661 0.01884 0.01400 -0.1394 0.7739 0.0502
-0.750 0.5945 0.01786 0.01297 -0.1400 0.7640 0.0513
-0.500 0.6239 0.01706 0.01206 -0.1405 0.7522 0.0537
-0.250 0.6569 0.01596 0.01062 -0.1410 0.7398 0.0593
0.000 0.6856 0.01512 0.00972 -0.1415 0.7247 0.0610
0.250 0.7224 0.01215 0.00598 -0.1418 0.7089 0.0420
0.500 0.7510 0.01149 0.00509 -0.1418 0.6857 0.0422
0.750 0.7786 0.01126 0.00466 -0.1416 0.6571 0.0417
1.000 0.8067 0.01079 0.00402 -0.1416 0.6317 0.0415
1.500 0.8623 0.01032 0.00331 -0.1415 0.5902 0.0432
1.750 0.8900 0.01032 0.00324 -0.1415 0.5726 0.0448
2.000 0.9175 0.01037 0.00323 -0.1414 0.5567 0.0469
2.250 0.9450 0.01044 0.00323 -0.1414 0.5421 0.0508
2.500 0.9724 0.01056 0.00331 -0.1413 0.5277 0.0564
3.000 1.0272 0.01074 0.00347 -0.1412 0.4972 0.0989
3.250 1.0543 0.01086 0.00359 -0.1412 0.4805 0.1201
3.500 1.0748 0.00957 0.00386 -0.1400 0.4632 1.0000
3.750 1.1008 0.00987 0.00397 -0.1397 0.4318 1.0000
4.000 1.1253 0.01032 0.00416 -0.1392 0.3883 1.0000
4.500 1.1737 0.01127 0.00472 -0.1382 0.3355 1.0000
4.750 1.1987 0.01165 0.00499 -0.1378 0.3209 1.0000
5.000 1.2239 0.01198 0.00526 -0.1375 0.3079 1.0000
5.250 1.2494 0.01227 0.00549 -0.1372 0.2960 1.0000
5.500 1.2747 0.01258 0.00574 -0.1368 0.2846 1.0000
5.750 1.2996 0.01290 0.00601 -0.1364 0.2728 1.0000
6.000 1.3244 0.01322 0.00627 -0.1360 0.2570 1.0000
6.250 1.3486 0.01358 0.00655 -0.1355 0.2368 1.0000
6.500 1.3685 0.01435 0.00702 -0.1344 0.1883 1.0000
6.750 1.3835 0.01557 0.00787 -0.1325 0.1310 1.0000
7.000 1.3965 0.01691 0.00885 -0.1304 0.0760 1.0000
7.250 1.4174 0.01746 0.00937 -0.1293 0.0700 1.0000
7.500 1.4386 0.01795 0.00989 -0.1283 0.0676 1.0000
7.750 1.4586 0.01850 0.01046 -0.1271 0.0655 1.0000
8.000 1.4774 0.01909 0.01110 -0.1258 0.0638 1.0000
8.250 1.4954 0.01970 0.01174 -0.1243 0.0623 1.0000
8.500 1.5119 0.02036 0.01245 -0.1225 0.0609 1.0000
8.750 1.5260 0.02112 0.01327 -0.1204 0.0593 1.0000
9.000 1.5396 0.02176 0.01398 -0.1181 0.0584 1.0000
9.250 1.5534 0.02243 0.01472 -0.1160 0.0575 1.0000
9.500 1.5664 0.02319 0.01555 -0.1139 0.0566 1.0000
9.750 1.5788 0.02403 0.01647 -0.1118 0.0556 1.0000
10.000 1.5902 0.02499 0.01749 -0.1097 0.0542 1.0000
10.250 1.5998 0.02611 0.01868 -0.1076 0.0525 1.0000
10.500 1.6050 0.02760 0.02023 -0.1050 0.0507 1.0000
10.750 1.6060 0.02948 0.02220 -0.1022 0.0491 1.0000
11.000 1.6252 0.02997 0.02277 -0.1014 0.0479 1.0000
11.250 1.6414 0.03069 0.02357 -0.1003 0.0460 1.0000
11.500 1.6559 0.03156 0.02450 -0.0992 0.0436 1.0000
11.750 1.6621 0.03315 0.02612 -0.0973 0.0411 1.0000
12.000 1.6881 0.03308 0.02610 -0.0973 0.0370 1.0000
12.250 1.7081 0.03350 0.02650 -0.0967 0.0315 1.0000
12.500 1.7213 0.03452 0.02747 -0.0955 0.0259 1.0000
13.000 1.7305 0.03817 0.03117 -0.0920 0.0213 1.0000
13.250 1.7320 0.04038 0.03345 -0.0903 0.0201 1.0000
13.500 1.7304 0.04296 0.03610 -0.0885 0.0192 1.0000
13.750 1.7267 0.04586 0.03910 -0.0868 0.0185 1.0000
14.000 1.7252 0.04864 0.04202 -0.0855 0.0181 1.0000
14.250 1.7223 0.05170 0.04520 -0.0844 0.0176 1.0000
14.500 1.7180 0.05505 0.04868 -0.0835 0.0172 1.0000
14.750 1.7128 0.05870 0.05245 -0.0829 0.0168 1.0000
15.000 1.7062 0.06268 0.05654 -0.0826 0.0164 1.0000
15.250 1.6974 0.06710 0.06107 -0.0825 0.0161 1.0000
15.500 1.6867 0.07192 0.06601 -0.0827 0.0158 1.0000
15.750 1.6739 0.07717 0.07137 -0.0831 0.0155 1.0000
16.000 1.6599 0.08268 0.07700 -0.0837 0.0153 1.0000
16.250 1.6484 0.08784 0.08228 -0.0844 0.0151 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)