GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 200,000 Max Cl/Cd: 75.21 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe329-il-200000-n5.txt Download as CSV file: xf-goe329-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2669 0.11214 0.10861 -0.0375 1.0000 0.0258
-9.500 -0.2679 0.10979 0.10632 -0.0388 1.0000 0.0259
-9.250 -0.2751 0.10805 0.10465 -0.0397 0.9993 0.0260
-9.000 -0.2573 0.10347 0.10006 -0.0401 0.9959 0.0263
-8.750 -0.2412 0.09981 0.09640 -0.0422 0.9896 0.0268
-8.500 -0.2260 0.09627 0.09285 -0.0456 0.9816 0.0273
-8.250 -0.2107 0.09269 0.08927 -0.0494 0.9727 0.0279
-8.000 -0.1953 0.08908 0.08565 -0.0535 0.9610 0.0287
-7.750 -0.1808 0.08547 0.08201 -0.0578 0.9463 0.0296
-7.500 -0.1687 0.08191 0.07840 -0.0647 0.9278 0.0306
-7.250 -0.1484 0.07733 0.07371 -0.0772 0.9107 0.0310
-7.000 -0.1368 0.07362 0.06997 -0.0777 0.8996 0.0312
-6.750 -0.1257 0.07074 0.06707 -0.0770 0.8897 0.0315
-6.500 -0.1116 0.06786 0.06414 -0.0781 0.8812 0.0320
-6.250 -0.0953 0.06491 0.06113 -0.0804 0.8718 0.0325
-6.000 -0.0767 0.06183 0.05798 -0.0834 0.8634 0.0333
-5.750 -0.0557 0.05862 0.05468 -0.0869 0.8547 0.0344
-5.500 -0.0107 0.05396 0.04959 -0.0983 0.8463 0.0371
-5.250 0.0054 0.05037 0.04596 -0.0990 0.8383 0.0375
-5.000 0.0230 0.04780 0.04337 -0.0994 0.8302 0.0380
-4.750 0.0441 0.04542 0.04089 -0.1004 0.8220 0.0388
-4.500 0.0683 0.04300 0.03836 -0.1020 0.8135 0.0399
-4.250 0.0952 0.04049 0.03566 -0.1038 0.8053 0.0417
-4.000 0.1338 0.03721 0.03184 -0.1073 0.7968 0.0450
-3.750 0.1542 0.03498 0.02963 -0.1077 0.7881 0.0461
-3.500 0.1785 0.03333 0.02792 -0.1083 0.7782 0.0480
-3.250 0.2149 0.03176 0.02571 -0.1097 0.7692 0.0538
-3.000 0.2382 0.02925 0.02322 -0.1104 0.7588 0.0549
-2.750 0.2639 0.02771 0.02161 -0.1109 0.7478 0.0566
-2.500 0.2937 0.02671 0.02031 -0.1112 0.7363 0.0620
-2.250 0.3216 0.02481 0.01816 -0.1119 0.7242 0.0658
-1.750 0.3841 0.02082 0.01332 -0.1119 0.6971 0.0459
-1.500 0.4124 0.01965 0.01195 -0.1119 0.6810 0.0420
-1.250 0.4417 0.01837 0.01027 -0.1117 0.6640 0.0388
-1.000 0.4705 0.01797 0.00945 -0.1113 0.6456 0.0371
-0.750 0.4980 0.01711 0.00841 -0.1112 0.6264 0.0367
-0.500 0.5253 0.01651 0.00760 -0.1110 0.6062 0.0365
-0.250 0.5524 0.01605 0.00693 -0.1108 0.5861 0.0365
0.000 0.5792 0.01568 0.00638 -0.1105 0.5671 0.0366
0.250 0.6062 0.01544 0.00595 -0.1103 0.5496 0.0374
0.500 0.6327 0.01503 0.00549 -0.1102 0.5341 0.0387
0.750 0.6594 0.01483 0.00521 -0.1100 0.5197 0.0392
1.000 0.6861 0.01466 0.00497 -0.1098 0.5060 0.0393
1.250 0.7130 0.01454 0.00480 -0.1097 0.4935 0.0396
1.500 0.7399 0.01446 0.00468 -0.1097 0.4823 0.0401
1.750 0.7668 0.01445 0.00461 -0.1096 0.4725 0.0407
2.000 0.7940 0.01445 0.00456 -0.1096 0.4631 0.0416
2.250 0.8208 0.01452 0.00456 -0.1095 0.4546 0.0428
2.500 0.8478 0.01459 0.00459 -0.1094 0.4459 0.0456
2.750 0.8745 0.01470 0.00464 -0.1093 0.4383 0.0490
3.000 0.9014 0.01482 0.00472 -0.1092 0.4307 0.0520
3.250 0.9279 0.01497 0.00486 -0.1091 0.4245 0.0622
3.750 0.9719 0.01364 0.00526 -0.1069 0.4127 1.0000
4.000 0.9982 0.01390 0.00545 -0.1067 0.4071 1.0000
4.250 1.0247 0.01414 0.00566 -0.1066 0.4010 1.0000
4.500 1.0507 0.01442 0.00588 -0.1064 0.3956 1.0000
4.750 1.0769 0.01469 0.00612 -0.1063 0.3908 1.0000
5.000 1.1032 0.01494 0.00640 -0.1062 0.3859 1.0000
5.250 1.1290 0.01523 0.00667 -0.1060 0.3813 1.0000
5.500 1.1545 0.01555 0.00696 -0.1058 0.3772 1.0000
5.750 1.1805 0.01581 0.00729 -0.1056 0.3723 1.0000
6.000 1.2061 0.01610 0.00761 -0.1054 0.3678 1.0000
6.250 1.2313 0.01644 0.00794 -0.1052 0.3640 1.0000
6.500 1.2567 0.01677 0.00832 -0.1049 0.3605 1.0000
6.750 1.2821 0.01707 0.00871 -0.1047 0.3565 1.0000
7.000 1.3067 0.01738 0.00908 -0.1044 0.3514 1.0000
7.250 1.3302 0.01772 0.00944 -0.1038 0.3446 1.0000
7.500 1.3531 0.01799 0.00979 -0.1032 0.3353 1.0000
7.750 1.3754 0.01831 0.01015 -0.1025 0.3260 1.0000
8.000 1.3962 0.01867 0.01051 -0.1015 0.3152 1.0000
8.250 1.4174 0.01900 0.01093 -0.1007 0.3030 1.0000
8.500 1.4381 0.01938 0.01138 -0.0997 0.2910 1.0000
8.750 1.4564 0.01984 0.01186 -0.0984 0.2740 1.0000
9.000 1.4729 0.02041 0.01241 -0.0969 0.2528 1.0000
9.250 1.4820 0.02139 0.01322 -0.0943 0.2102 1.0000
9.500 1.4637 0.02399 0.01516 -0.0881 0.1187 1.0000
9.750 1.4497 0.02668 0.01752 -0.0831 0.0679 1.0000
10.000 1.4424 0.02906 0.01973 -0.0795 0.0369 1.0000
10.250 1.4440 0.03092 0.02162 -0.0771 0.0300 1.0000
10.500 1.4470 0.03275 0.02355 -0.0751 0.0267 1.0000
10.750 1.4487 0.03479 0.02569 -0.0732 0.0247 1.0000
11.000 1.4520 0.03678 0.02784 -0.0717 0.0234 1.0000
11.250 1.4534 0.03905 0.03025 -0.0703 0.0223 1.0000
11.500 1.4528 0.04161 0.03295 -0.0690 0.0214 1.0000
11.750 1.4494 0.04458 0.03606 -0.0679 0.0207 1.0000
12.000 1.4428 0.04806 0.03968 -0.0671 0.0200 1.0000
12.250 1.4358 0.05177 0.04353 -0.0666 0.0194 1.0000
12.500 1.4315 0.05533 0.04724 -0.0663 0.0189 1.0000
12.750 1.4254 0.05922 0.05129 -0.0663 0.0184 1.0000
13.000 1.4185 0.06340 0.05561 -0.0666 0.0179 1.0000
13.250 1.4109 0.06781 0.06017 -0.0670 0.0176 1.0000
13.500 1.4030 0.07236 0.06486 -0.0676 0.0172 1.0000
13.750 1.3949 0.07701 0.06963 -0.0683 0.0169 1.0000
14.000 1.3874 0.08161 0.07434 -0.0690 0.0166 1.0000
14.250 1.3803 0.08616 0.07900 -0.0697 0.0164 1.0000
14.500 1.3737 0.09061 0.08354 -0.0705 0.0161 1.0000
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Polar data table (+)
Polar graphs
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