GOE 429 AIRFOIL (goe429-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 429 AIRFOIL (goe429-il) Reynolds number: 200,000 Max Cl/Cd: 47.45 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe429-il-200000.txt Download as CSV file: xf-goe429-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 429 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -1.0715 0.09481 0.09077 0.0150 1.0000 0.0323
-14.500 -1.1002 0.08558 0.08136 0.0090 1.0000 0.0320
-14.250 -1.1262 0.07730 0.07288 0.0035 1.0000 0.0319
-14.000 -1.1492 0.07001 0.06535 -0.0013 1.0000 0.0319
-13.750 -1.1692 0.06368 0.05877 -0.0051 1.0000 0.0319
-13.500 -1.1859 0.05824 0.05306 -0.0081 1.0000 0.0320
-13.250 -1.1999 0.05356 0.04811 -0.0102 1.0000 0.0322
-13.000 -1.2111 0.04966 0.04391 -0.0114 1.0000 0.0324
-12.750 -1.2143 0.04596 0.04007 -0.0113 1.0000 0.0330
-12.500 -1.2109 0.04349 0.03753 -0.0108 1.0000 0.0336
-12.250 -1.2068 0.04145 0.03540 -0.0098 1.0000 0.0344
-12.000 -1.1998 0.03945 0.03326 -0.0089 1.0000 0.0352
-11.750 -1.1906 0.03739 0.03100 -0.0080 1.0000 0.0364
-11.500 -1.1793 0.03544 0.02879 -0.0072 1.0000 0.0378
-11.250 -1.1664 0.03331 0.02648 -0.0063 1.0000 0.0394
-11.000 -1.1492 0.03201 0.02522 -0.0058 1.0000 0.0413
-10.750 -1.1314 0.03069 0.02375 -0.0052 1.0000 0.0437
-10.500 -1.1136 0.02900 0.02185 -0.0044 1.0000 0.0463
-10.250 -1.0942 0.02774 0.02064 -0.0040 1.0000 0.0493
-10.000 -1.0729 0.02679 0.01947 -0.0035 1.0000 0.0538
-9.750 -1.0524 0.02559 0.01835 -0.0031 1.0000 0.0586
-9.500 -1.0304 0.02455 0.01715 -0.0026 1.0000 0.0649
-9.250 -1.0073 0.02383 0.01644 -0.0024 1.0000 0.0709
-9.000 -0.9842 0.02286 0.01539 -0.0021 1.0000 0.0774
-8.750 -0.9596 0.02230 0.01474 -0.0020 1.0000 0.0839
-8.500 -0.9357 0.02129 0.01369 -0.0017 1.0000 0.0899
-8.250 -0.9105 0.02065 0.01301 -0.0016 1.0000 0.0963
-8.000 -0.8858 0.01971 0.01203 -0.0013 1.0000 0.1026
-7.750 -0.8604 0.01904 0.01134 -0.0012 1.0000 0.1097
-7.500 -0.8352 0.01815 0.01045 -0.0011 1.0000 0.1170
-7.250 -0.8092 0.01748 0.00976 -0.0010 1.0000 0.1245
-7.000 -0.7837 0.01661 0.00894 -0.0008 1.0000 0.1319
-6.750 -0.7570 0.01600 0.00830 -0.0007 1.0000 0.1405
-6.500 -0.7309 0.01527 0.00767 -0.0007 1.0000 0.1509
-6.250 -0.7040 0.01465 0.00714 -0.0007 1.0000 0.1648
-6.000 -0.6767 0.01408 0.00664 -0.0007 1.0000 0.1854
-5.750 -0.6497 0.01344 0.00616 -0.0008 1.0000 0.2166
-5.500 -0.6226 0.01285 0.00574 -0.0010 1.0000 0.2513
-5.250 -0.5948 0.01241 0.00540 -0.0012 1.0000 0.2812
-5.000 -0.5667 0.01205 0.00513 -0.0013 1.0000 0.3082
-4.750 -0.5384 0.01172 0.00491 -0.0015 1.0000 0.3326
-4.500 -0.5096 0.01145 0.00469 -0.0018 1.0000 0.3570
-4.250 -0.4810 0.01117 0.00452 -0.0020 1.0000 0.3812
-4.000 -0.4519 0.01094 0.00436 -0.0024 1.0000 0.4064
-3.750 -0.4228 0.01070 0.00423 -0.0028 1.0000 0.4305
-3.500 -0.3934 0.01050 0.00413 -0.0033 1.0000 0.4556
-3.250 -0.3647 0.01032 0.00407 -0.0038 1.0000 0.4803
-3.000 -0.3331 0.01020 0.00405 -0.0051 0.9913 0.5052
-2.750 -0.2903 0.01011 0.00404 -0.0080 0.9679 0.5325
-2.500 -0.2547 0.01008 0.00409 -0.0093 0.9444 0.5561
-2.250 -0.2274 0.01014 0.00419 -0.0086 0.9219 0.5778
-2.000 -0.2034 0.01023 0.00427 -0.0072 0.9006 0.5990
-1.750 -0.1803 0.01031 0.00436 -0.0055 0.8809 0.6174
-1.500 -0.1567 0.01037 0.00441 -0.0040 0.8622 0.6343
-1.250 -0.1320 0.01041 0.00442 -0.0027 0.8447 0.6505
-1.000 -0.1062 0.01044 0.00442 -0.0017 0.8284 0.6661
-0.750 -0.0801 0.01046 0.00441 -0.0009 0.8126 0.6815
-0.500 -0.0536 0.01046 0.00440 -0.0001 0.7967 0.6966
-0.250 -0.0273 0.01045 0.00438 0.0007 0.7806 0.7113
0.000 -0.0011 0.01043 0.00435 0.0016 0.7638 0.7258
0.250 0.0250 0.01041 0.00432 0.0026 0.7464 0.7401
0.500 0.0516 0.01036 0.00428 0.0033 0.7274 0.7543
0.750 0.0781 0.01031 0.00425 0.0041 0.7081 0.7697
1.000 0.1041 0.01026 0.00423 0.0051 0.6886 0.7877
1.250 0.1299 0.01020 0.00419 0.0061 0.6684 0.8065
1.500 0.1558 0.01013 0.00414 0.0070 0.6464 0.8242
1.750 0.1816 0.01003 0.00408 0.0080 0.6196 0.8411
2.000 0.2071 0.00996 0.00401 0.0090 0.5876 0.8580
2.250 0.2317 0.00992 0.00393 0.0102 0.5473 0.8765
2.500 0.2563 0.00997 0.00387 0.0114 0.4957 0.8986
2.750 0.2833 0.01019 0.00388 0.0119 0.4396 0.9265
3.000 0.3186 0.01055 0.00400 0.0104 0.3844 0.9605
3.250 0.3585 0.01097 0.00418 0.0075 0.3365 1.0000
3.500 0.3875 0.01137 0.00436 0.0067 0.3045 1.0000
3.750 0.4166 0.01175 0.00457 0.0061 0.2803 1.0000
4.000 0.4455 0.01213 0.00481 0.0056 0.2620 1.0000
4.250 0.4743 0.01247 0.00507 0.0053 0.2472 1.0000
4.500 0.5030 0.01279 0.00534 0.0050 0.2342 1.0000
4.750 0.5315 0.01311 0.00562 0.0047 0.2226 1.0000
5.000 0.5597 0.01345 0.00590 0.0045 0.2121 1.0000
5.250 0.5882 0.01369 0.00617 0.0044 0.2016 1.0000
5.500 0.6165 0.01392 0.00643 0.0042 0.1901 1.0000
5.750 0.6449 0.01412 0.00664 0.0041 0.1747 1.0000
6.000 0.6731 0.01437 0.00684 0.0039 0.1545 1.0000
6.250 0.7008 0.01477 0.00715 0.0039 0.1241 1.0000
6.500 0.7278 0.01544 0.00764 0.0038 0.0902 1.0000
6.750 0.7541 0.01619 0.00826 0.0039 0.0772 1.0000
7.000 0.7803 0.01693 0.00899 0.0039 0.0715 1.0000
7.250 0.8059 0.01774 0.00980 0.0041 0.0676 1.0000
7.500 0.8301 0.01880 0.01083 0.0043 0.0649 1.0000
7.750 0.8551 0.01966 0.01175 0.0046 0.0634 1.0000
8.000 0.8797 0.02058 0.01275 0.0049 0.0617 1.0000
8.250 0.9038 0.02158 0.01379 0.0053 0.0599 1.0000
8.500 0.9273 0.02269 0.01491 0.0056 0.0581 1.0000
8.750 0.9504 0.02404 0.01625 0.0061 0.0568 1.0000
9.000 0.9729 0.02587 0.01809 0.0066 0.0555 1.0000
9.250 0.9959 0.02744 0.01980 0.0070 0.0546 1.0000
9.500 1.0188 0.02868 0.02123 0.0075 0.0535 1.0000
9.750 1.0407 0.03018 0.02293 0.0080 0.0524 1.0000
10.000 1.0615 0.03192 0.02488 0.0085 0.0515 1.0000
10.250 1.0810 0.03374 0.02690 0.0090 0.0505 1.0000
10.500 1.0999 0.03560 0.02889 0.0095 0.0492 1.0000
10.750 1.1172 0.03771 0.03113 0.0099 0.0481 1.0000
11.000 1.1322 0.04051 0.03407 0.0104 0.0472 1.0000
11.250 1.1421 0.04427 0.03809 0.0109 0.0467 1.0000
11.500 1.1432 0.04915 0.04333 0.0114 0.0462 1.0000
11.750 1.1402 0.05190 0.04644 0.0123 0.0459 1.0000
12.000 1.1316 0.05495 0.04983 0.0131 0.0456 1.0000
12.250 1.1143 0.05844 0.05358 0.0136 0.0455 1.0000
12.500 1.0938 0.06303 0.05840 0.0121 0.0455 1.0000
12.750 1.0709 0.06884 0.06443 0.0089 0.0457 1.0000
13.000 1.0459 0.07594 0.07171 0.0046 0.0459 1.0000
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Polar data table (+)
Polar graphs
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