GOE 460 AIRFOIL (goe460-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 460 AIRFOIL (goe460-il) Reynolds number: 100,000 Max Cl/Cd: 34.06 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe460-il-100000-n5.txt Download as CSV file: xf-goe460-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 460 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.500 -0.7995 0.12857 0.12171 -0.0450 1.0000 0.0862
-19.250 -0.7700 0.13080 0.12402 -0.0435 1.0000 0.0874
-19.000 -0.7829 0.12507 0.11824 -0.0461 1.0000 0.0900
-18.750 -0.8630 0.10773 0.10052 -0.0545 1.0000 0.0938
-18.500 -0.8844 0.10114 0.09378 -0.0572 1.0000 0.0962
-18.250 -0.8780 0.09922 0.09190 -0.0575 1.0000 0.0986
-18.000 -0.8880 0.09468 0.08727 -0.0591 1.0000 0.1014
-17.750 -0.9077 0.08871 0.08111 -0.0613 1.0000 0.1044
-17.500 -0.9150 0.08480 0.07711 -0.0624 1.0000 0.1071
-17.250 -0.9131 0.08238 0.07472 -0.0627 1.0000 0.1102
-17.000 -0.9203 0.07863 0.07090 -0.0636 1.0000 0.1135
-16.750 -0.9330 0.07417 0.06625 -0.0647 1.0000 0.1169
-16.500 -0.9316 0.07184 0.06398 -0.0648 1.0000 0.1202
-16.250 -0.9354 0.06885 0.06097 -0.0651 1.0000 0.1237
-16.000 -0.9426 0.06545 0.05745 -0.0655 1.0000 0.1276
-15.750 -0.9459 0.06265 0.05462 -0.0655 1.0000 0.1313
-15.500 -0.9483 0.06013 0.05211 -0.0653 1.0000 0.1349
-15.250 -0.9530 0.05734 0.04925 -0.0652 1.0000 0.1390
-15.000 -0.9562 0.05480 0.04663 -0.0648 1.0000 0.1429
-14.750 -0.9582 0.05261 0.04446 -0.0642 1.0000 0.1467
-14.500 -0.9608 0.05036 0.04215 -0.0635 1.0000 0.1510
-14.250 -0.9630 0.04822 0.03992 -0.0626 1.0000 0.1556
-14.000 -0.9646 0.04638 0.03808 -0.0614 1.0000 0.1598
-13.750 -0.9660 0.04455 0.03618 -0.0601 1.0000 0.1647
-13.500 -0.9666 0.04289 0.03443 -0.0586 1.0000 0.1696
-13.250 -0.9670 0.04142 0.03296 -0.0569 1.0000 0.1741
-13.000 -0.9673 0.03998 0.03143 -0.0550 1.0000 0.1793
-12.750 -0.9673 0.03866 0.03004 -0.0529 1.0000 0.1844
-12.500 -0.9667 0.03752 0.02890 -0.0506 1.0000 0.1892
-12.250 -0.9672 0.03638 0.02767 -0.0481 1.0000 0.1947
-12.000 -0.9678 0.03533 0.02654 -0.0453 1.0000 0.2001
-11.750 -0.9676 0.03444 0.02569 -0.0424 1.0000 0.2052
-11.500 -0.9699 0.03355 0.02474 -0.0390 1.0000 0.2110
-11.250 -0.9726 0.03273 0.02384 -0.0354 1.0000 0.2167
-11.000 -0.9737 0.03205 0.02323 -0.0318 1.0000 0.2220
-10.750 -0.9778 0.03140 0.02254 -0.0277 1.0000 0.2278
-10.250 -0.9847 0.03028 0.02140 -0.0192 1.0000 0.2384
-10.000 -0.9892 0.02981 0.02093 -0.0146 1.0000 0.2434
-9.750 -0.9940 0.02938 0.02043 -0.0099 1.0000 0.2484
-9.500 -0.9816 0.02885 0.01990 -0.0082 0.9976 0.2544
-9.250 -0.9526 0.02829 0.01933 -0.0096 0.9921 0.2617
-9.000 -0.9269 0.02774 0.01866 -0.0103 0.9859 0.2690
-8.750 -0.8981 0.02723 0.01821 -0.0115 0.9807 0.2757
-8.500 -0.8737 0.02675 0.01769 -0.0117 0.9743 0.2832
-8.250 -0.8471 0.02628 0.01722 -0.0124 0.9682 0.2907
-8.000 -0.8204 0.02585 0.01679 -0.0130 0.9626 0.2987
-7.750 -0.7977 0.02543 0.01633 -0.0126 0.9550 0.3065
-7.500 -0.7676 0.02500 0.01594 -0.0138 0.9502 0.3150
-7.250 -0.7499 0.02464 0.01556 -0.0124 0.9413 0.3239
-7.000 -0.7228 0.02423 0.01518 -0.0128 0.9353 0.3345
-6.750 -0.7035 0.02388 0.01486 -0.0116 0.9272 0.3451
-6.500 -0.6799 0.02349 0.01446 -0.0112 0.9198 0.3585
-6.250 -0.6471 0.02304 0.01406 -0.0125 0.9155 0.3730
-6.000 -0.6355 0.02276 0.01383 -0.0096 0.9041 0.3848
-5.750 -0.6035 0.02233 0.01342 -0.0107 0.8992 0.4002
-5.500 -0.5888 0.02206 0.01313 -0.0083 0.8888 0.4138
-5.250 -0.5580 0.02168 0.01281 -0.0090 0.8828 0.4286
-5.000 -0.5320 0.02137 0.01254 -0.0086 0.8754 0.4423
-4.750 -0.5091 0.02110 0.01228 -0.0077 0.8664 0.4562
-4.500 -0.4745 0.02072 0.01188 -0.0089 0.8614 0.4714
-4.250 -0.4577 0.02057 0.01178 -0.0067 0.8501 0.4825
-4.000 -0.4243 0.02025 0.01146 -0.0077 0.8440 0.4953
-3.750 -0.4036 0.02006 0.01125 -0.0062 0.8340 0.5071
-3.500 -0.3728 0.01982 0.01104 -0.0066 0.8262 0.5183
-3.250 -0.3433 0.01957 0.01075 -0.0068 0.8189 0.5304
-3.000 -0.3208 0.01943 0.01064 -0.0056 0.8082 0.5410
-2.750 -0.2840 0.01914 0.01034 -0.0071 0.8021 0.5530
-2.500 -0.2693 0.01908 0.01028 -0.0044 0.7894 0.5640
-2.250 -0.2327 0.01885 0.01007 -0.0059 0.7825 0.5754
-2.000 -0.2187 0.01878 0.00997 -0.0031 0.7700 0.5868
-1.750 -0.1808 0.01859 0.00982 -0.0048 0.7626 0.5975
-1.500 -0.1648 0.01853 0.00977 -0.0024 0.7502 0.6084
-1.250 -0.1281 0.01837 0.00963 -0.0037 0.7424 0.6200
-1.000 -0.1094 0.01838 0.00969 -0.0018 0.7301 0.6322
-0.750 -0.0814 0.01827 0.00958 -0.0015 0.7211 0.6472
-0.500 -0.0559 0.01831 0.00970 -0.0007 0.7094 0.6603
-0.250 -0.0264 0.01830 0.00972 -0.0007 0.6985 0.6732
0.000 -0.0001 0.01825 0.00965 0.0000 0.6869 0.6868
0.250 0.0265 0.01831 0.00972 0.0006 0.6735 0.6984
0.500 0.0560 0.01831 0.00969 0.0007 0.6604 0.7093
0.750 0.0813 0.01827 0.00958 0.0015 0.6473 0.7212
1.000 0.1095 0.01838 0.00969 0.0018 0.6322 0.7301
1.250 0.1280 0.01837 0.00963 0.0038 0.6199 0.7424
1.500 0.1648 0.01853 0.00976 0.0024 0.6084 0.7501
1.750 0.1808 0.01859 0.00982 0.0047 0.5975 0.7626
2.000 0.2188 0.01878 0.00997 0.0031 0.5869 0.7700
2.250 0.2326 0.01884 0.01006 0.0059 0.5754 0.7825
2.500 0.2693 0.01908 0.01028 0.0045 0.5639 0.7895
2.750 0.2841 0.01914 0.01035 0.0071 0.5530 0.8021
3.000 0.3208 0.01943 0.01064 0.0056 0.5409 0.8082
3.250 0.3434 0.01957 0.01075 0.0068 0.5304 0.8188
3.500 0.3729 0.01982 0.01104 0.0066 0.5183 0.8262
3.750 0.4036 0.02006 0.01125 0.0062 0.5071 0.8341
4.000 0.4244 0.02025 0.01146 0.0076 0.4953 0.8440
4.250 0.4577 0.02057 0.01178 0.0067 0.4824 0.8501
4.500 0.4746 0.02072 0.01189 0.0089 0.4714 0.8614
4.750 0.5091 0.02109 0.01227 0.0077 0.4561 0.8665
5.000 0.5320 0.02137 0.01253 0.0086 0.4424 0.8753
5.250 0.5582 0.02168 0.01280 0.0089 0.4287 0.8828
5.500 0.5887 0.02206 0.01312 0.0083 0.4137 0.8888
5.750 0.6037 0.02233 0.01341 0.0106 0.4001 0.8992
6.000 0.6357 0.02276 0.01383 0.0096 0.3847 0.9042
6.250 0.6475 0.02304 0.01406 0.0125 0.3732 0.9155
6.500 0.6799 0.02349 0.01445 0.0112 0.3583 0.9198
6.750 0.7037 0.02387 0.01485 0.0116 0.3451 0.9273
7.000 0.7231 0.02422 0.01518 0.0127 0.3344 0.9353
7.250 0.7501 0.02464 0.01555 0.0123 0.3238 0.9413
7.500 0.7681 0.02499 0.01594 0.0137 0.3151 0.9502
7.750 0.7982 0.02542 0.01633 0.0126 0.3064 0.9550
8.000 0.8205 0.02584 0.01678 0.0129 0.2985 0.9627
8.250 0.8474 0.02628 0.01721 0.0123 0.2905 0.9683
8.500 0.8741 0.02674 0.01768 0.0117 0.2831 0.9744
8.750 0.8987 0.02722 0.01820 0.0114 0.2756 0.9808
9.000 0.9276 0.02773 0.01865 0.0102 0.2689 0.9860
9.250 0.9535 0.02828 0.01932 0.0095 0.2617 0.9921
9.500 0.9824 0.02884 0.01988 0.0081 0.2543 0.9977
9.750 0.9940 0.02936 0.02041 0.0098 0.2484 1.0000
10.000 0.9891 0.02979 0.02091 0.0146 0.2433 1.0000
10.250 0.9849 0.03026 0.02138 0.0191 0.2384 1.0000
10.500 0.9840 0.03077 0.02178 0.0231 0.2333 1.0000
10.750 0.9780 0.03138 0.02251 0.0277 0.2277 1.0000
11.000 0.9740 0.03203 0.02321 0.0318 0.2220 1.0000
11.250 0.9729 0.03271 0.02381 0.0354 0.2166 1.0000
11.500 0.9703 0.03353 0.02471 0.0390 0.2110 1.0000
11.750 0.9681 0.03441 0.02566 0.0423 0.2052 1.0000
12.000 0.9686 0.03529 0.02650 0.0452 0.2002 1.0000
12.250 0.9684 0.03633 0.02761 0.0480 0.1949 1.0000
12.500 0.9675 0.03748 0.02886 0.0505 0.1892 1.0000
12.750 0.9679 0.03863 0.02999 0.0528 0.1844 1.0000
13.000 0.9684 0.03993 0.03137 0.0549 0.1794 1.0000
13.250 0.9679 0.04138 0.03291 0.0568 0.1740 1.0000
13.500 0.9678 0.04283 0.03436 0.0585 0.1696 1.0000
13.750 0.9673 0.04450 0.03611 0.0600 0.1647 1.0000
14.000 0.9654 0.04634 0.03804 0.0613 0.1596 1.0000
14.250 0.9643 0.04815 0.03985 0.0625 0.1555 1.0000
14.500 0.9621 0.05031 0.04209 0.0634 0.1508 1.0000
14.750 0.9595 0.05254 0.04439 0.0641 0.1466 1.0000
15.000 0.9580 0.05470 0.04653 0.0647 0.1429 1.0000
15.250 0.9542 0.05731 0.04921 0.0650 0.1387 1.0000
15.500 0.9499 0.06005 0.05203 0.0652 0.1347 1.0000
15.750 0.9478 0.06255 0.05450 0.0653 0.1311 1.0000
16.000 0.9440 0.06542 0.05743 0.0653 0.1273 1.0000
16.250 0.9373 0.06877 0.06088 0.0649 0.1236 1.0000
16.500 0.9339 0.07171 0.06384 0.0646 0.1201 1.0000
16.750 0.9354 0.07404 0.06612 0.0645 0.1168 1.0000
17.000 0.9224 0.07854 0.07080 0.0634 0.1133 1.0000
17.250 0.9159 0.08221 0.07454 0.0625 0.1100 1.0000
17.500 0.9185 0.08453 0.07682 0.0622 0.1070 1.0000
17.750 0.9088 0.08882 0.08123 0.0610 0.1041 1.0000
18.000 0.8907 0.09456 0.08715 0.0589 0.1012 1.0000
18.250 0.8811 0.09905 0.09172 0.0573 0.0984 1.0000
18.500 0.8888 0.10076 0.09338 0.0571 0.0960 1.0000
18.750 0.8642 0.10791 0.10071 0.0541 0.0937 1.0000
19.000 0.7898 0.12424 0.11739 0.0462 0.0899 1.0000
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