GOE 798 AIRFOIL (goe798-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 798 AIRFOIL (goe798-il) Reynolds number: 200,000 Max Cl/Cd: 61.72 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe798-il-200000-n5.txt Download as CSV file: xf-goe798-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 798 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.4890 0.05076 0.04534 -0.1479 0.9191 0.0557
-13.250 -0.5383 0.04107 0.03519 -0.1563 0.9048 0.0559
-13.000 -0.5539 0.03746 0.03131 -0.1573 0.8936 0.0562
-12.750 -0.5516 0.03578 0.02955 -0.1565 0.8842 0.0565
-12.500 -0.5493 0.03442 0.02811 -0.1550 0.8738 0.0569
-12.250 -0.5459 0.03325 0.02682 -0.1530 0.8644 0.0574
-12.000 -0.5408 0.03224 0.02573 -0.1509 0.8538 0.0579
-11.750 -0.5305 0.03117 0.02452 -0.1495 0.8452 0.0586
-11.500 -0.5202 0.03013 0.02333 -0.1479 0.8355 0.0594
-11.250 -0.5075 0.02900 0.02201 -0.1466 0.8274 0.0603
-11.000 -0.4944 0.02788 0.02067 -0.1453 0.8192 0.0613
-10.750 -0.4775 0.02703 0.01970 -0.1442 0.8114 0.0621
-10.500 -0.4575 0.02644 0.01904 -0.1435 0.8046 0.0628
-10.250 -0.4379 0.02588 0.01841 -0.1426 0.7968 0.0637
-10.000 -0.4171 0.02526 0.01767 -0.1419 0.7902 0.0647
-9.750 -0.3962 0.02461 0.01688 -0.1411 0.7840 0.0659
-9.500 -0.3756 0.02389 0.01599 -0.1404 0.7778 0.0673
-9.250 -0.3524 0.02349 0.01552 -0.1399 0.7724 0.0684
-9.000 -0.3279 0.02319 0.01516 -0.1395 0.7679 0.0697
-8.750 -0.3046 0.02284 0.01476 -0.1390 0.7626 0.0711
-8.500 -0.2811 0.02236 0.01415 -0.1385 0.7575 0.0729
-8.250 -0.2566 0.02196 0.01363 -0.1381 0.7529 0.0745
-8.000 -0.2304 0.02177 0.01336 -0.1379 0.7489 0.0760
-7.750 -0.2060 0.02152 0.01307 -0.1375 0.7442 0.0780
-7.500 -0.1814 0.02110 0.01251 -0.1371 0.7399 0.0808
-7.250 -0.1553 0.02100 0.01238 -0.1369 0.7360 0.0825
-7.000 -0.1289 0.02081 0.01210 -0.1367 0.7325 0.0849
-6.750 -0.1020 0.02047 0.01155 -0.1366 0.7294 0.0882
-6.500 -0.0766 0.02034 0.01144 -0.1363 0.7255 0.0901
-6.250 -0.0511 0.02019 0.01124 -0.1360 0.7214 0.0928
-6.000 -0.0249 0.01999 0.01085 -0.1357 0.7177 0.0964
-5.750 0.0016 0.01979 0.01067 -0.1356 0.7144 0.0985
-5.500 0.0289 0.01963 0.01046 -0.1356 0.7115 0.1012
-5.250 0.0571 0.01947 0.01014 -0.1358 0.7088 0.1043
-5.000 0.0825 0.01926 0.00991 -0.1354 0.7054 0.1068
-4.750 0.1081 0.01909 0.00977 -0.1351 0.7018 0.1091
-4.500 0.1344 0.01893 0.00959 -0.1349 0.6983 0.1118
-4.250 0.1614 0.01879 0.00936 -0.1348 0.6952 0.1145
-4.000 0.1888 0.01859 0.00910 -0.1348 0.6925 0.1168
-3.750 0.2168 0.01839 0.00890 -0.1350 0.6899 0.1191
-3.500 0.2443 0.01825 0.00875 -0.1350 0.6871 0.1215
-3.250 0.2694 0.01814 0.00865 -0.1346 0.6836 0.1240
-3.000 0.2954 0.01806 0.00853 -0.1343 0.6801 0.1265
-2.750 0.3214 0.01786 0.00837 -0.1340 0.6766 0.1294
-2.500 0.3482 0.01772 0.00824 -0.1339 0.6729 0.1325
-2.250 0.3768 0.01759 0.00805 -0.1341 0.6692 0.1355
-2.000 0.4024 0.01749 0.00793 -0.1337 0.6650 0.1375
-1.750 0.4267 0.01740 0.00785 -0.1330 0.6605 0.1389
-1.500 0.4520 0.01725 0.00773 -0.1326 0.6562 0.1407
-1.250 0.4785 0.01711 0.00760 -0.1324 0.6523 0.1430
-1.000 0.5070 0.01699 0.00744 -0.1325 0.6488 0.1455
-0.750 0.5310 0.01694 0.00742 -0.1318 0.6443 0.1477
-0.500 0.5543 0.01688 0.00738 -0.1310 0.6388 0.1503
-0.250 0.5796 0.01680 0.00729 -0.1305 0.6339 0.1531
0.000 0.6070 0.01669 0.00719 -0.1305 0.6300 0.1572
0.250 0.6330 0.01666 0.00717 -0.1302 0.6265 0.1627
0.500 0.6559 0.01666 0.00726 -0.1293 0.6222 0.1699
0.750 0.6799 0.01663 0.00731 -0.1287 0.6180 0.1824
1.000 0.7050 0.01656 0.00732 -0.1283 0.6141 0.2034
1.250 0.7318 0.01646 0.00730 -0.1282 0.6106 0.2359
1.500 0.7554 0.01639 0.00738 -0.1275 0.6064 0.2746
1.750 0.7761 0.01634 0.00753 -0.1264 0.6011 0.3202
2.000 0.7982 0.01618 0.00760 -0.1254 0.5962 0.3900
2.250 0.8210 0.01583 0.00764 -0.1246 0.5917 0.5181
2.500 0.8378 0.01549 0.00786 -0.1224 0.5868 0.6844
2.750 0.8700 0.01536 0.00828 -0.1227 0.5808 0.8942
3.000 0.9250 0.01555 0.00845 -0.1284 0.5750 0.9866
3.250 0.9603 0.01572 0.00855 -0.1303 0.5695 1.0000
3.500 0.9717 0.01590 0.00872 -0.1272 0.5630 1.0000
3.750 0.9865 0.01604 0.00879 -0.1247 0.5568 1.0000
4.000 0.9992 0.01619 0.00889 -0.1218 0.5507 1.0000
4.250 1.0081 0.01642 0.00912 -0.1183 0.5433 1.0000
4.500 1.0231 0.01661 0.00922 -0.1159 0.5362 1.0000
4.750 1.0347 0.01690 0.00951 -0.1131 0.5279 1.0000
5.000 1.0487 0.01719 0.00973 -0.1107 0.5190 1.0000
5.250 1.0617 0.01755 0.01007 -0.1083 0.5094 1.0000
5.500 1.0757 0.01791 0.01034 -0.1061 0.4994 1.0000
5.750 1.0884 0.01837 0.01078 -0.1037 0.4883 1.0000
6.000 1.1017 0.01885 0.01118 -0.1016 0.4779 1.0000
6.250 1.1144 0.01940 0.01167 -0.0994 0.4666 1.0000
6.500 1.1270 0.02000 0.01221 -0.0973 0.4558 1.0000
7.000 1.1514 0.02134 0.01343 -0.0932 0.4350 1.0000
7.250 1.1633 0.02209 0.01409 -0.0912 0.4258 1.0000
7.500 1.1757 0.02286 0.01483 -0.0893 0.4165 1.0000
7.750 1.1871 0.02370 0.01559 -0.0874 0.4081 1.0000
8.000 1.1996 0.02453 0.01640 -0.0858 0.3997 1.0000
8.250 1.2111 0.02543 0.01721 -0.0840 0.3921 1.0000
8.500 1.2241 0.02630 0.01807 -0.0825 0.3851 1.0000
8.750 1.2368 0.02719 0.01893 -0.0811 0.3785 1.0000
9.000 1.2499 0.02807 0.01974 -0.0797 0.3731 1.0000
9.250 1.2650 0.02889 0.02058 -0.0786 0.3685 1.0000
9.500 1.2798 0.02974 0.02144 -0.0775 0.3639 1.0000
9.750 1.2940 0.03062 0.02231 -0.0764 0.3595 1.0000
10.000 1.3086 0.03148 0.02312 -0.0753 0.3554 1.0000
10.250 1.3237 0.03235 0.02401 -0.0743 0.3516 1.0000
10.500 1.3383 0.03327 0.02498 -0.0734 0.3478 1.0000
10.750 1.3527 0.03421 0.02594 -0.0725 0.3440 1.0000
11.000 1.3666 0.03517 0.02689 -0.0715 0.3400 1.0000
11.250 1.3814 0.03606 0.02773 -0.0706 0.3362 1.0000
11.500 1.3950 0.03710 0.02884 -0.0697 0.3329 1.0000
11.750 1.4083 0.03818 0.02999 -0.0688 0.3294 1.0000
12.000 1.4205 0.03933 0.03118 -0.0679 0.3255 1.0000
12.250 1.4337 0.04040 0.03226 -0.0670 0.3220 1.0000
12.500 1.4484 0.04132 0.03317 -0.0663 0.3187 1.0000
12.750 1.4617 0.04243 0.03431 -0.0655 0.3156 1.0000
13.000 1.4723 0.04379 0.03578 -0.0646 0.3123 1.0000
13.250 1.4832 0.04511 0.03719 -0.0638 0.3089 1.0000
13.500 1.4941 0.04643 0.03855 -0.0630 0.3053 1.0000
13.750 1.5059 0.04763 0.03975 -0.0622 0.3018 1.0000
14.000 1.5183 0.04881 0.04093 -0.0615 0.2983 1.0000
14.250 1.5242 0.05068 0.04294 -0.0606 0.2943 1.0000
14.500 1.5310 0.05246 0.04482 -0.0598 0.2900 1.0000
14.750 1.5394 0.05406 0.04646 -0.0590 0.2860 1.0000
15.000 1.5493 0.05546 0.04784 -0.0583 0.2822 1.0000
15.250 1.5533 0.05760 0.05013 -0.0575 0.2777 1.0000
15.500 1.5563 0.05985 0.05250 -0.0567 0.2725 1.0000
15.750 1.5610 0.06190 0.05457 -0.0560 0.2674 1.0000
16.000 1.5647 0.06411 0.05684 -0.0554 0.2625 1.0000
16.250 1.5653 0.06672 0.05958 -0.0548 0.2565 1.0000
16.500 1.5667 0.06920 0.06209 -0.0542 0.2507 1.0000
16.750 1.5663 0.07198 0.06498 -0.0536 0.2443 1.0000
17.000 1.5637 0.07503 0.06808 -0.0531 0.2371 1.0000
17.250 1.5620 0.07802 0.07113 -0.0527 0.2301 1.0000
17.500 1.5580 0.08130 0.07446 -0.0523 0.2224 1.0000
17.750 1.5540 0.08460 0.07781 -0.0520 0.2153 1.0000
18.000 1.5490 0.08805 0.08127 -0.0518 0.2080 1.0000
18.250 1.5442 0.09150 0.08475 -0.0516 0.2016 1.0000
18.500 1.5393 0.09497 0.08824 -0.0516 0.1955 1.0000
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Polar data table (+)
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